Boundary layer effect turbine

ABSTRACT

Described herein are embodiments of a boundary layer effect turbine and a hydrodynamic speed reducer. Described is a boundary layer effect turbine that utilizes the phenomena of the boundary layer to drive a turbine impeller that is made of a plurality of spaced disks oriented along a rotatable shaft. As operating fluid is directed over surfaces of the plurality of disks of the boundary layer effect turbine, energy is transferred from the fluid to the disks as a result of the adhesive and viscous properties of the fluid.

RELATED APPLICATIONS

The present application is a §371 national phase application filing ofApplication No. PCT/US2008/088687, with an international filing date ofDec. 31, 2008, and which claims priority benefit from U.S. ProvisionalApplication No. 61/018,089, filed Dec. 31, 2007, the entire contents ofboth of which are hereby incorporated herein by reference.

FIELD OF THE DISCLOSURE

The present disclosure relates to a boundary layer effect gasmicroturbine for the purpose of producing a torque for mechanical workor to generate electric power.

BACKGROUND OF THE DISCLOSURE

Reciprocating internal combustion engines have long been used to replaceman power with that of the machine. In these engines, a linear motion isimparted to one or more reciprocating pistons by compression andignition of a mixture of fuel and air. The linear motion of the one ormore pistons is converted to rotational motion by connection of aconnecting rod to a crankshaft. The rotation motion is then used, forexample, for mechanical work or generation of electric power.

An alternative to the reciprocating internal combustion engine is therotary engine. For example, the bladed turbine engine has been utilizedin several industries, including for propulsion of aircraft andwatercraft and for power generation. In contrast to the internalcombustion engine, rotary engines replace the piston, connecting rod,and crankshaft with a rotor assembly, a rotating unit. Rotary enginesoperate differently than the internal combustion engine, but also resultin rotational motion that is used, for example, for mechanical work orgeneration of electric power.

SUMMARY OF THE DISCLOSURE

The internal combustion engine and the bladed turbine engine each sufferfrom respective shortcomings that are addressed by embodiments of thedisclosure provided herein. These shortcomings include their complexconstruction and inherent inefficient operations.

Described herein is a boundary layer effect turbine that utilizes thephenomena of the boundary layer to drive a turbine impeller that is madeof a plurality of spaced disks oriented along a rotatable shaft. Asoperating fluid is directed over surfaces of the plurality of disks ofthe boundary layer effect turbine, energy is transferred from the fluidto the disks as a result of the adhesive and viscous properties of thefluid. The boundary layer effect turbine directs the operating fluid ina radially-converging spiral, or vortical, path through narrow spacesbetween the plurality of disks and drives the shaft for the generationof electric power or for mechanical work. As explained further below,the boundary layer effect turbine of this disclosure providesembodiments that enhance the operation of the microturbine beyond thecapabilities of the internal combustion engine or blade turbine.

In some embodiments, a modified boundary layer turbine is described thatincludes a housing having a fluid inlet port and a fluid outlet port; acentral shaft, extending through the housing, the central shaft defininga central axis; and a plurality of annular disks within the housing,each of the disks being spaced apart from an adjacent disk by means, insome embodiments, of an airfoil shaped spacer, each spacer presenting apositive surface, which induces a near positive displacement of thefluid moving between the disks, each of the disks having an inneropening through which the central shaft extends and having an outeredge; wherein the outer edge of at least one of the of annular disks istapered; wherein the plurality of annular disks is configured in thehousing to transmit kinetic energy between at least one of the disks, asit rotates about the central shaft, and fluid introduced into thehousing through the fluid inlet port, the transmission of kinetic energyresulting, at least in part, from a boundary layer formed at a surfaceof the at least one of the disks.

In some embodiments, at least one of the annular disks further comprisesa tapered inner edge. In some embodiments, the fluid inlet port is alongthe central axis, and in some embodiments with the fluid inlet portalong the central axis, the fluid outlet port is adjacent an outer edgeof at least one of the plurality of disks. In some embodiments, thefluid outlet port is along the central axis.

In some embodiments, the modified boundary layer turbine furthercomprises a fluid heat exchanger in communication with the fluid outletport and the fluid inlet port. In some embodiments, the modifiedboundary layer turbine further comprises a combustion chamber thatdirects fluid toward the fluid inlet port.

In some embodiments, rotation of the plurality of annular disks isconfigured to transmit kinetic energy from the rotating disks to thefluid. In some embodiments, the plurality of annular disks areconfigured to rotate upon transmission of kinetic energy from the fluid.In some embodiments, the central shaft is supported by at least onemagnetic bearing, and in some embodiments, the central shaft issupported by at least one air bearing.

In some embodiments, a modified boundary layer turbine is described,comprising a housing having a fluid inlet port and a fluid outlet port;a central shaft, extending through the housing, the central shaftdefining a central axis; and a plurality of annular disks within thehousing, each of the disks being spaced apart from an adjacent disk,each of the disks having an inner opening through which the centralshaft extends and having an outer edge; wherein the inner edge of atleast one of the of annular disks is tapered; wherein the plurality ofannular disks is configured in the housing to transmit kinetic energybetween at least one of the disks, as it rotates about the centralshaft, and fluid introduced into the housing through the fluid inletport, the transmission of kinetic energy resulting, at least in part,from a boundary layer formed at a surface of the at least one of thedisks.

In some embodiments, a modified boundary layer compressor is describedthat includes a housing having a fluid inlet port and a fluid outletport; a central shaft, extending through the housing, the central shaftdefining a central axis; and a plurality of annular disks within thehousing, each of the disks being spaced apart from an adjacent disk bymeans of an airfoil shaped spacer, each spacer presenting a positivesurface, which induces a near positive displacement of the fluid movingbetween the disks, each of the disks having an inner opening throughwhich the central shaft extends and having an outer edge; wherein theouter edge of at least one of the of annular disks is tapered; whereinthe plurality of annular disks is configured in the housing to transmitkinetic energy between at least one of the disks, as it rotates aboutthe central shaft, and fluid introduced into the housing through thefluid inlet port, the transmission of kinetic energy resulting, at leastin part, from a boundary layer formed at a surface of at least one ofthe disks.

Some embodiments describe a modified boundary layer compressor,comprising a housing having a fluid inlet port and a fluid outlet port;a central shaft, extending through the housing through the inlet andoutlet ports, the central shaft defining a central axis; a plurality ofannular disks within the housing, each of the disks having a face andbeing spaced apart from an adjacent disk such that the faces of thedisks are substantially parallel; wherein each of the disks has amodified outer edge, and an inner opening through which the centralshaft extends; wherein the plurality of annular disks is configured inthe housing to transmit kinetic energy between at least one of thedisks, as it rotates about the central shaft, and fluid introduced intothe housing through the fluid inlet port, the transmission of kineticenergy resulting, at least in part, from a boundary layer formed at theface of at least one of the disks; and a plurality of elongate, arcuateelevations extending along the face of at least one of the disks, eachof the arcuate elevations having a first region and a second region;wherein the first region of each of the arcuate elevations is locatedcloser to the central axis than is the second region of the same arcuateelevation; and wherein each of the arcuate elevations tapers in width asit extends from the first region to the second region, such that a widthof each of the arcuate elevations at its first region is greater than awidth of the same arcuate elevation at its second region.

In some embodiments, at least one of the annular disks further comprisesa tapered inner edge. In some embodiments, the fluid inlet port is alongthe central axis, and in some embodiments with the fluid inlet portalong the central axis, the fluid outlet port is adjacent an outer edgeof at least one of the plurality of disks.

Certain embodiments described herein provide a boundary layercompressor, comprising a housing having a fluid inlet port and a fluidoutlet port; a central drive shaft, extending through a central portionof the housing, the central drive shaft defining a central axis; aplurality of annular disks, within the housing, arrayed along andcoupled to the central drive shaft; wherein each of the plurality of theannular disks has a front face and a rear face and is positioned alongthe central axis such that a plurality of substantially parallel annularspaces is defined between adjacent faces of the plurality of the annulardisks; wherein the plurality of the annular disks define a cylindricalspace located central to inner edges of the annular disks, thecylindrical space containing the central drive shaft; a blade memberextending, in the cylindrical space, from the central drive shaft towardthe inner edges of the annular disks, the blade member further extendinghelically about the central axis; wherein, during rotation of thecentral drive shaft, fluid located in the annular spaces is drawn in thedirection of rotation in a boundary layer within the annular spaces; andwherein, during rotation of the central drive shaft, fluid in thecylindrical space is received along the cylindrical space from the fluidinlet port and directed radially outwardly through the annular spaces.

Some embodiments described herein provide a disk compressor assembly,comprising a plurality of substantially parallel annular disks, axiallyspaced along a rotation axis, the annular disks defining a cylindricalspace extending through a center portion of the annular disks andbounded by inner edges of the annular disks; wherein the plurality ofannular disks define a plurality of annular spaces between adjacent ofthe annular disks; and a blade member extending, in the cylindricalspace, from the rotation axis toward inner edges of the annular disks,the blade member further extending helically about the rotation axis;wherein, during use, the plurality of annular disks rotates, and fluidis received into the cylindrical space, in a substantially axialdirection, and the fluid flows between the annular disks, in asubstantially radial direction, into the annular spaces.

Some embodiments described herein provide a disk compressor assembly,comprising a plurality of substantially parallel annular disks, axiallyspaced along a rotation axis, the annular disks defining a cylindricalspace extending through a center portion of the annular disks andbounded by inner edges of the annular disks; wherein the plurality ofannular disks define a plurality of annular spaces between adjacent ofthe annular disks; and a blade member extending, in the cylindricalspace, from the rotation axis toward inner edges of the annular disks,the blade member further extending helically about the rotation axis;wherein, during use, the plurality of annular disks rotates, and fluidis received into the cylindrical space, in a substantially axialdirection, and the fluid flows between the annular disks, in asubstantially radial direction, into the annular spaces.

In some embodiments, a disk compressor assembly comprises a plurality ofsubstantially parallel annular disks, axially spaced along a rotationaxis, the annular disks having an outer edge and defining a cylindricalspace extending through a center portion of the annular disks that isbounded by inner edges of the annular disks; wherein the plurality ofannular disks define a plurality of annular spaces between adjacent ofthe annular disks; and a blade member extending, in the cylindricalspace, from the rotation axis toward inner edges of the annular disks,the blade member further extending helically about the rotation axis; afluid inlet located adjacent the outer edge of at least one of theplurality of annular disks and a fluid outlet located adjacent thecylindrical space; wherein, during use, fluid travels along a vorticalflow path within at least one of the plurality of annular spaces fromthe fluid inlet to the cylindrical space, and then along a helical,axial flow path through the cylindrical space toward the fluid outlet.

Described herein are embodiments of a gas compressor based on the use ofa driven rotor consisting of a plurality of flat disks utilizing theboundary layer phenomenon, which relies on the cohesive and viscosityproperties of a gaseous fluid, combined with aerofoil shaped spacersbetween said disks to give a near positive displacement effect at highrotating speeds is presented herein. In using this method to compressinlet gas, the disk compressor efficiently achieves high compressionratios. The embodiments described herein include single, double, andmultiple stage compression cycles. In the two stage versions, the gasflows radially outward accelerating the gas, converting velocity intopressure as the gas slows down in a circumferential diffuser. The gas issubsequently returned in a radially inward cycle, forcing the gas into areduced volume at high speed to increase the pressure, after which thegas is allowed to expand into the recuperator volume that acts as apressure sink. Multiple stages repeat the principles described above toobtain higher-pressure ratios.

In some embodiments, the fluid inlet port is along the central axis, andin some embodiments, the fluid inlet port is adjacent to an outer edgeof at least one of the plurality of disks. Some embodiments provide thatrotation of the plurality of annular disks is configured to transmitkinetic energy from the rotating disks to the fluid. In someembodiments, the plurality of annular disks are configured to rotateupon transmission of kinetic energy from the fluid. In some embodiments,the central shaft is supported by at least one magnetic bearing, and insome embodiments, the central shaft is supported by at least one airbearing.

Some embodiments describe a modified boundary layer turbine, comprisinga housing having a fluid inlet port and a fluid outlet port; a centralshaft, extending through the housing, the central shaft defining acentral axis; a plurality of annular disks within the housing, each ofthe disks having a face and being spaced apart from an adjacent disksuch that the faces of the disks are substantially parallel; whereineach of the disks has an outer edge, and an inner opening through whichthe central shaft extends; wherein the plurality of annular disks isconfigured in the housing to transmit kinetic energy between at leastone of the disks, as it rotates about the central shaft, and fluidintroduced into the housing through the fluid inlet port, thetransmission of kinetic energy resulting, at least in part, from aboundary layer formed at the face of at least one of the disks; and aplurality of elongate, arcuate elevations extending along the face of atleast one of the disks, each of the arcuate elevations having a firstregion and a second region; wherein the first region of each of thearcuate elevations is located closer to the central axis than is thesecond region of the same arcuate elevation; and wherein each of thearcuate elevations tapers in width as it extends from the first regionto the second region, such that a width of each of the arcuateelevations at its first region is greater than a width of the samearcuate elevation at its second region.

Some embodiments provide that the arcuate elevation comprisessubstantially an airfoil shape. In some embodiments, the arcuateelevation has a thickness equal to the space between adjacent disks, andin some embodiments, the arcuate elevation has a thickness greater thanthe boundary layer space between adjacent disks. Some embodimentsprovide that during rotation of the central shaft, the plurality ofarcuate elevations directs fluid flowing across the face of the disk ina radially outward direction, and in some embodiments, during rotationof the central shaft, the plurality of arcuate elevations directs fluidflowing across the face of the disk in a radially inward direction. Insome embodiments, the arcuate elevations present a surface, whichinduces a near positive displacement of the fluid moving between thedisks, enhancing the mechanical efficiency of the boundary layer effect.In some embodiments, at least one of the arcuate elevations comprises athickness equal to about twice the thickness of a laminar flow boundarylayer of a fluid that flows into the housing from the fluid inlet portand across the face of at least one of the disks. In some embodiments,at least two of the disks are spaced about 0.6 mm apart, and in someembodiments, at least two of the disks are spaced about 1.2 mm apart.

Some embodiments provide that at least one of the arcuate elevations areintegrally formed with at least one of the plurality of annular disks.In some embodiments, at least one of the arcuate elevations comprises adifferent material than does the at least one of the disks. In someembodiments, the central shaft is supported by at least one magneticbearing, and in some embodiments, the central shaft is supported by atleast one air bearing.

Certain embodiments described herein provide a boundary layer turbine,comprising a housing having a fluid inlet port and a fluid outlet port;a central drive shaft, extending through a central portion of thehousing, the central drive shaft defining a central axis; a plurality ofannular disks, within the housing, arrayed along and coupled to thecentral drive shaft; wherein each of the plurality of the annular diskshas a front face and a rear face and is positioned along the centralaxis such that a plurality of substantially parallel annular spaces isdefined between adjacent faces of the plurality of the annular disks;wherein the plurality of the annular disks define a cylindrical spacelocated central to inner edges of the annular disks, the cylindricalspace containing the central drive shaft; a blade member extending, inthe cylindrical space, from the central drive shaft toward the inneredges of the annular disks, the blade member further extending helicallyabout the central axis; wherein, during rotation of the central driveshaft, fluid located in the annular spaces is drawn in the direction ofrotation in a boundary layer within the annular spaces; and wherein,during rotation of the central drive shaft, fluid in the cylindricalspace is received along the cylindrical space from the fluid inlet portand directed radially outwardly through the annular spaces.

In certain embodiments of the boundary layer turbine, the blade memberhas width that extends from an interior edge of the blade member,located adjacent the central shaft, to an outer edge of the blade memberthat is closer to at least one of the plurality of the annular disksthan is the interior edge; wherein the blade member is curved along itswidth. In some embodiments, the inner edge of at least one of theplurality of the annular disks is tapered. In some embodiments, an outeredge of at least one of the plurality of the annular disks is tapered.In some embodiments, the inner edge of at least one of the plurality ofthe annular disks is tapered. Some embodiments provide that at least oneof the plurality of the annular disks comprises a plurality of elongate,arcuate elevations extending along the face of the at least one of thedisks, each of the arcuate elevations having a first region and a secondregion; wherein the first region of each of the arcuate elevations islocated closer to the central axis than is the second region of the samearcuate elevation; and wherein each of the arcuate elevations tapers inwidth as it extends from the first region to the second region, suchthat a width of each of the arcuate elevations at its first region isgreater than a width of the same arcuate elevation at its second region.

In some embodiments, the boundary layer turbine further comprises aplurality of blade members extending, in the cylindrical space, from thecentral drive shaft toward the inner edges of the annular disks, each ofthe plurality of blade members further extending helically about thecentral axis. In some embodiments, the central shaft is supported,during rotation, by at least one magnetic bearing, and in someembodiments, the central shaft is supported, during rotation, by atleast one air bearing.

Some embodiments described herein provide a disk turbine assembly,comprising a plurality of substantially parallel annular disks, axiallyspaced along a rotation axis, the annular disks defining a cylindricalspace extending through a center portion of the annular disks andbounded by inner edges of the annular disks; wherein the plurality ofannular disks define a plurality of annular spaces between adjacent ofthe annular disks; and a blade member extending, in the cylindricalspace, from the rotation axis toward inner edges of the annular disks,the blade member further extending helically about the rotation axis;wherein, during use, the plurality of annular disks rotates, and fluidis received into the cylindrical space, in a substantially axialdirection, and the fluid flows between the annular disks, in asubstantially radial direction, into the annular spaces.

In some embodiments, the blade member width extends from an interioredge of the blade member, located adjacent the rotation axis, to anouter edge of the blade member that is closer to at least one of theplurality of the annular disks than is the interior edge; wherein theblade member is curved along its width. In some embodiments, the inneredge of at least one of the plurality of the annular disks is tapered.In some embodiments, an outer edge of at least one of the plurality ofthe annular disks is tapered, and in some of these embodiments, theinner edge of the at least one of the plurality of the annular disks istapered.

In certain embodiments, at least one of the plurality of the annulardisks comprises a plurality of elongate, arcuate elevations extendingalong a face of the at least one of the disks, each of the arcuateelevations having a first region and a second region; wherein the firstregion of each of the arcuate elevations is located closer to therotation axis than is the second region of the same arcuate elevation;and wherein each of the arcuate elevations tapers in width as it extendsfrom the first region to the second region, such that a width of each ofthe arcuate elevations at its first region is greater than a width ofthe same arcuate elevation at its second region.

In some embodiments, the disk turbine assembly further comprising aplurality of blade members extending, in the cylindrical space, from therotation axis toward the inner edges of the annular disks, each of theplurality of blade members further extending helically about therotation axis.

Some embodiments describe a disk turbine impeller, comprising aplurality of substantially parallel annular disks, axially spaced alonga rotation axis, the annular disks defining a cylindrical spaceextending through a center portion of the annular disks and bounded byinner edges of the annular disks; wherein the plurality of annular disksdefine a plurality of annular spaces between adjacent of the annulardisks; and a plurality of axial vanes that extend, within thecylindrical space, toward the inner edges of the annular disks from therotation axis; wherein the axial vanes are oriented helically about therotation axis.

Some embodiments provide that the blade member has a width that extendsfrom an interior edge of the blade member, located adjacent the rotationaxis, to an outer edge of the blade member that is closer to at leastone of the plurality of the annular disks than is the interior edge;wherein the blade member is curved along its width. In some embodiments,the inner edge of at least one of the plurality of the annular disks istapered. In certain embodiments, an outer edge of at least one of theplurality of the annular disks is tapered, and in some of theseembodiments, the inner edge of the at least one of the plurality of theannular disks is tapered.

Some embodiments provide that at least one of the plurality of theannular disks comprises a plurality of elongate, arcuate elevationsextending along a face of the at least one of the disks, each of thearcuate elevations having a first region and a second region; whereinthe first region of each of the arcuate elevations is located closer tothe rotation axis than is the second region of the same arcuateelevation; and wherein each of the arcuate elevations tapers in width asit extends from the first region to the second region, such that a widthof each of the arcuate elevations at its first region is greater than awidth of the same arcuate elevation at its second region. In someembodiments, the disk turbine assembly further comprises a plurality ofblade members extending, in the cylindrical space, from the rotationaxis toward the inner edges of the annular disks, each of the pluralityof blade members further extending helically about the rotation axis.

In some embodiments, a disk turbine assembly, comprises a plurality ofsubstantially parallel annular disks, axially spaced along a rotationaxis, the annular disks having an outer edge and defining a cylindricalspace extending through a center portion of the annular disks that isbounded by inner edges of the annular disks; wherein the plurality ofannular disks define a plurality of annular spaces between adjacent ofthe annular disks; and a blade member extending, in the cylindricalspace, from the rotation axis toward inner edges of the annular disks,the blade member further extending helically about the rotation axis; afluid inlet located adjacent the outer edge of at least one of theplurality of annular disks and a fluid outlet located adjacent thecylindrical space; wherein, during use, fluid travels along a vorticalflow path within at least one of the plurality of annular spaces fromthe fluid inlet to the cylindrical space, and then along a helical,axial flow path through the cylindrical space toward the fluid outlet.

In some embodiments, the inner edge of at least one of the annular disksis tapered, and in some embodiments, the outer edge of at least one ofthe annular disks is tapered. In certain embodiments, the blade memberhas width that extends from an interior edge of the blade member,located adjacent the rotation axis, to an outer edge of the blade memberthat is closer to at least one of the plurality of the annular disksthan is the interior edge; wherein the blade member is curved along itswidth.

In some embodiments, at least one of the plurality of the annular diskscomprises a plurality of elongate, arcuate elevations extending along aface of the at least one of the disks, each of the arcuate elevationshaving a first region and a second region; wherein the first region ofeach of the arcuate elevations is located closer to the rotation axisthan is the second region of the same arcuate elevation; and whereineach of the arcuate elevations tapers in width as it extends from thefirst region to the second region, such that a width of each of thearcuate elevations at its first region is greater than a width of thesame arcuate elevation at its second region. In some embodiments, thedisk turbine assembly further comprises a plurality of blade membersextending, in the cylindrical space, from the rotation axis toward theinner edges of the annular disks, each of the plurality of blade membersfurther extending helically about the rotation axis.

Some embodiments described herein provide a high speed permanent magnetstarter generator which is mounted on the same shaft as other rotatingassemblies. Some embodiments provide for the starter generator to bewater cooled by water having a temperature lower than the ambienttemperature in order to reduce the compressor inlet air temperature andenhancing compressor efficiency. In some embodiments, the casing of thestarter generator may be provided with extended surfaces or fins tofacilitate heat exchanging.

Some embodiments described herein provide a high speed hydrodynamicspeed reducer that comprises a housing defining an internal chamber witha central axis; a cylindrical drive element within the internal chamber,the drive element being aligned along the central axis and having ahelical recess along an outer surface of the drive element that definesa fluid drive flow path, the drive element being configured to couplewith a rotatable speed reducer input; a driven element within theinternal chamber, the driven element being aligned along the centralaxis and having a cylindrical bore with an internal surface having ahelical recess that defines a fluid driven flow path, the driven elementbeing configured to couple with a rotatable speed reducer output; atubular divider element within the internal chamber and aligned alongthe central axis, the divider element having a first end and a secondend and being positioned between the outer surface of the cylindricaldrive element and the internal surface of the driven element; andoperating fluid within the internal chamber, the fluid drive flow path,and the fluid driven flow path; wherein rotation of the speed reduceroutput is achieved by rotating the speed reducer input, which rotatesthe drive element and drives the operating fluid in a first axialdirection along the fluid drive flow path, around the first end of thetubular divider, in a second axial direction along the fluid driven flowpath, rotating the driven element, around the second end of the tubulardivider, and into the fluid drive flow path.

Some embodiments include a combustor, for a boundary layer turbine, thatincludes a primary venturi burner, at least one secondary venturiburner, and a controller that directs flow of fluid through the primaryventuri burner, the at least one secondary venturi burner, and through apassage that is not through a burner.

Some embodiments provide that the rotatable speed reducer input issupported by an air bearing, and some embodiments provide that therotatable speed reducer input is supported by a magnetic bearing. Insome embodiments, an operating fluid outlet, through which operatingfluid is directed to an external oil cooler. In some embodiments, thecylindrical drive element comprises a plurality of helical recessesalong the outer surface that defines a plurality of fluid drive flowpaths. In some embodiments, the cylindrical bore of the driven elementcomprises a plurality of helical recesses along the internal surfacethat defines a plurality of fluid driven flow paths. In someembodiments, the helical recess along the outer surface of the driveelement and the helical recess along the internal surface of the drivenelement are arranged such that rotation of the cylindrical drive elementin a first rotational direction results in rotation of the drivenelement in a second rotation direction that is opposite the firstrotation direction. In certain embodiments, the operating fluidcomprises a synthetic oil with spherical inorganic nanoparticleproperties that cause the oil to stay cool without loosing itslubricity. In some embodiments, the drive element is configured tocouple with the rotatable speed reducer input by a magnetic drive. Insome embodiments, the rotatable speed reducer input rotates the driveelement through a magnetic drive.

BRIEF DESCRIPTION OF THE DRAWINGS

A general architecture that implements the various features of thedisclosure will now be described with reference to the drawings. Thedrawings and the associated descriptions are provided to illustrateembodiments of the disclosure and not to limit the scope of thedisclosure. Throughout the drawings, reference numbers are re-used toindicate correspondence between referenced elements.

FIG. 1A is a schematic front view of embodiments of a disk used inconnection with a boundary layer effect turbine.

FIG. 1B is a schematic side view of embodiments of a series of disks,such as those illustrated in FIG. 1A, assembled along a turbine shaft.

FIG. 2 is a schematic side view of embodiments of airflow across aturbine disk surface, comparing the profile of laminar flow to that ofturbulent flow.

FIG. 3 is a diagram schematically showing embodiments of flow of fluidthrough embodiments of a boundary layer effect turbine.

FIG. 4 depicts side, front, and rear views of embodiments of a boundarylayer effect turbine.

FIG. 5A is a partial cross-sectional view of an embodiments of aboundary layer effect turbine.

FIG. 5B is another partial cross-sectional view of an embodiments of aboundary layer effect turbine, showing, among other things, schematicviews of components of the turbine.

FIG. 6A illustrates a partial view of embodiments of the boundary layereffect turbine of FIG. 4, showing, among other things, the arrangementof the water cooled starter generator with magnetic bearings on eitherside of it placed in the air flow path into the compressor.

FIG. 6B illustrates a partial view of embodiments of a boundary layereffect turbine, illustrating the direction of fluid flow through theturbine with arrows.

FIG. 7 illustrates a schematic side view of embodiments of a compressorin connection with a boundary layer effect turbine.

FIG. 8A illustrates a schematic front view of a portion of thecompressor of FIG. 7.

FIG. 8B illustrates embodiments of a disk used in impeller embodimentsdescribed herein.

FIG. 8C illustrates embodiments of a compressor using two sets of disks.

FIG. 8D illustrates embodiments of a disk used in impeller embodimentsdescribed herein.

FIG. 8E illustrates a rear view of embodiments of a compressor.

FIG. 8F illustrates schematic embodiments of a compressor using aplurality of compressor impellors.

FIG. 8G illustrates a schematic view of an embodiment of a three-stagecompressor that can be used in connection with a boundary layer effectturbine.

FIG. 8H illustrates a schematic view of an embodiment of a compressorthat can be used in connection with a boundary layer effect turbine.

FIG. 8I illustrates an image with schematic markings that depict theflow of fluid through a boundary layer effect.

FIG. 8J illustrates a front view of embodiments of a first stage of acompressor in use with a boundary layer effect turbine.

FIG. 8K illustrates embodiments of a second stage of a compressor inused with a boundary layer effect turbine.

FIG. 9A illustrates a schematic cross-sectional view of embodiments of apair of disks of a boundary layer effect turbine.

FIG. 9B illustrates a schematic cross-sectional view of embodiments of apair of disks of a boundary layer effect turbine.

FIG. 9C illustrates a schematic cross-sectional view of embodiments of apair of disks of a boundary layer effect turbine.

FIG. 10 illustrates a cross-sectional view of embodiments of a boundarylayer effect turbine, including a compressor, a recuperator, and turbineexpander.

FIG. 11 illustrates a partial cross-sectional side view of embodimentsof a recuperator used with a boundary layer effect turbine.

FIG. 12A illustrates a front view of embodiments of a recuperator usedwith a boundary layer effect turbine.

FIG. 12B illustrates a schematic partial cross-sectional side view ofembodiments of a recuperator used with a boundary layer effect turbine.

FIG. 12C illustrates a rear view of embodiments of a recuperator usedwith a boundary layer effect turbine.

FIG. 12D illustrates embodiments of a recuperator used with a boundarylayer effect turbine.

FIG. 12E illustrates embodiments of a recuperator used with a boundarylayer effect turbine.

FIG. 12F illustrates embodiments of a recuperator used with a boundarylayer effect turbine.

FIG. 12G illustrates embodiments of a recuperator used with a boundarylayer effect turbine.

FIG. 13A illustrates a schematic front view of embodiments of a turbineexpander with dashed arrows representing a flow path of air through aturbine expander scroll and across a face of the disk.

FIG. 13B illustrates a perspective view of embodiments of a turbineexpander casing.

FIG. 14 illustrates a schematic front view of embodiments of a turbineexpander with arrows representing a flow path of air through a turbineexpander scroll and through disks of the expander.

FIG. 15A is a perspective view of embodiments of a back plate havingcenter impeller vanes.

FIG. 15B is a perspective view of embodiments of a disk of a boundarylayer effect turbine.

FIG. 16A is a perspective view of a back plate with a plurality of disksassembled thereon.

FIG. 16B is an exploded view of the back plate and disks of FIG. 17A.

FIG. 17A is a schematic representation of spacing between disks of theboundary layer effect turbine.

FIG. 17B is a schematic representation of spacing between disks of theboundary layer effect turbine.

FIG. 18 is a schematic representation of a boundary layer effect turbineand peripheral components mounted inside its weatherproof cabinet.

FIG. 19A is a front schematic view of embodiments of a boundary layereffect turbine.

FIG. 19B is a rear schematic view of embodiments of a boundary layereffect turbine.

FIG. 20A is a longitudinal sectional view of embodiments of a combustorwith venturi secondary burners as well as a primary burner.

FIG. 20B is a partial cross sectional view of the combustor showing aplurality of venturi burners, a primary burner in the center, and anadjustable air bypass control ring around the assembly.

FIG. 20C is a sectional view showing a spark igniter and an axiallysupplied primary fuel supply and the radially supplied secondary fuelsupply to the venturi burners.

FIG. 21 is a perspective view of embodiments of a high speed reducerthat is operable with a boundary layer effect turbine.

FIG. 22 is an exploded view of embodiments of the high speed reducer ofFIG. 21.

FIG. 23A depicts embodiments of a high speed reducer.

FIG. 23B depicts embodiments of a high speed reducer.

FIG. 24 depicts embodiments of a general assembly of a disk turbinefitted with a hydrodynamic speed reducer.

FIG. 25 depicts an exemplary heating and air conditioning unit that canbe configured to operate in connection with a boundary layer effectturbine.

DETAILED DESCRIPTION OF THE DISCLOSURE

The boundary layer effect turbine described herein has severaladvantages over the internal combustion engine and the blade turbine.The internal combustion engine is a complex system that has severalmoving parts that are arranged about a rotating crankshaft. While theinternal combustion engine has been used for many purposes in manyindustries, the complex construction presents significant maintenancecomplications. Additionally, the reciprocating motion between variouscomponents of the internal combustion engine (e.g., the piston withinthe cylinder) results in the generation of heat caused by the frictionbetween parts. The heat results in losses that decrease the efficiencyof the internal combustion engine.

Similarly, the blade turbine is also plagued with complications arisingfrom its principle of operation. Cavitation occurs as the operatingfluid engages the blades moving at extremely high speeds. This damagesthe blades and presents different, but significant, maintenancecomplications, such as requiring replacement or resurfacing of theturbine blades. Additionally, the blades rotate at near sonic speeds andcreate turbulent air flow through the turbine, resulting in inherentlynoisy operation. The distances between turbine blades also result in alarge percentage of the fluid not making contact with the blades toimpart its kinetic energy to the blades, resulting in a significant lossin efficiency.

The boundary layer effect turbine provides a single rotation assemblythat operates to compress the operating fluid prior to combustion andutilizes the inherent adhesion and viscosity qualities of the fluid todrive the turbine. The total fluid flow is divided into extremely narrowsegments, each segment being twice the size of the boundary layer at thedisk surface, so as to maximize the transfer of kinetic energy atmolecular level to the surface of the disk. Described herein areembodiments of the boundary layer effect turbine that builds upon theseadvantages and further enhances the operational efficiency of theboundary layer effect turbine.

The boundary layer effect turbine operates on properties of theoperating fluid. All fluids, including a gaseous fluid, possess the twoproperties of viscosity and adhesion, which causes the molecules of thefluid to “stick” to the surface of the disks in a boundary layerinterfacing with the body surface. At that interface, the fluid flowapproaches zero relative speed to the surface, and the boundary layer isa transitional area extending from the body surface into the fluid. Atthe body surface the flow of the fluid with respect to the body surfaceapproaches zero velocity, and the flow of fluid at a periphery of theboundary layer is where the flow of fluid is about 99% of the rate ofthe free-flowing fluid. Throughout the boundary layer, shear stresses ofthe fluid caused by the viscosity of the operating fluid, create a dragon the body surface as the fluid on one side is pulled in one directionby the free-flowing fluid and on the other side by adherence to the bodysurface. These shear stresses transfer kinetic energy of the flowingfluid to the body surface as a function of the fluid's viscosity.

As used herein, the term boundary layer is a broad term and is used withits ordinary meaning, which includes, without limitation, a transitionallayer of fluid created when a fluid passes over a surface, thetransitional layer having varying velocities ranging from a positionadjacent or at the surface, where the velocity approaches zero withrespect to the surface, to a position adjacent the free-flowing fluid,where the velocity of the fluid within the boundary layer approachesthat of the free-flowing fluid. For example, in some embodiments, theboundary layer extends from the surface to a distance away from thesurface at which the fluid's velocity ranges from about 93% to about 99%of the velocity of the free-flowing fluid. In some embodiments, theboundary layer extends from the surface, or a point adjacent thesurface, to a distance away from the surface at which the fluid'svelocity is less than about 93% or greater than about 99% of thevelocity of the free-flowing fluid.

As used herein, the term free-flowing fluid is used is a broad term andis used with its ordinary meaning, which includes, without limitation,the fluid that is flowing with no or substantially no impedance causedby adjacent surfaces or structures. For example, the free-flowing fluidis that fluid that is not impeded by the stresses created by a boundarylayer when fluid passes over a surface.

The boundary layer effect turbine utilizes the phenomena of the boundarylayer to drive a rotor. As fluid is injected at high speeds directlyover surfaces of a plurality of disks of the boundary layer effectturbine, energy is transferred from the fluid to the disks. The boundarylayer effect turbine creates a vortex flow in a turbine expansionchamber by directing high velocity gas in a radially-converging spiralpath through narrow spaces between a plurality of disks axially spacedalong a rotating shaft. The fluid flow is introduced into the turbineexpansion chamber near a periphery of the disks and is directed, in someembodiments, slightly incident to the plurality of disks. The fluidpasses over one or more surfaces of the disk in vortical flow and isexpelled through an aperture or apertures located near or at the centerof the disks.

FIGS. 1A and 1B illustrate embodiments of a boundary layer effectturbine disk assembly 100. FIG. 1A illustrates a front view of aboundary layer effect turbine disk 102 having a plurality of exhaustapertures 105 positioned around a shaft 110 that extends through thecenter of the disk 102. A face of the disk 102 is substantially smoothand provides the body surface over which the operating fluid flows andupon which the boundary layer is created to transfer kinetic energybetween the disk and the operating fluid.

The disk edge 120 defines the outer periphery of the disk 102, and diskedges 120 of several disks 102 axially aligned along the shaft 110, asdepicted in FIG. 1B, define the outer periphery of the disk assembly.The shaft 110 defines an axis 125 that extends through the center ofeach of the disks 102, and the disks 102 are manufactured to be inrotational balance along the shaft 110 such that the disks 102 will beable to withstand the centripetal forces during rotation of the disks102 at high speeds. For example, in some applications of the embodimentsdisclosed herein, the disks 102 are configured to rotate at speeds offrom about 20,000 rpm to about 100,000 rpm. In some embodiments, thedisks 102 are configured to rotate at speeds of less than about 20,000rpm or greater than about 100,000 rpm. The speed of rotation isdetermined, at least in part, by the velocity of the fluid entering theperipheral spaces between the disks. The velocity of the fluid enteringthe peripheral spaces is determined, at least in part, by the amount offluid injected into the disk chamber during operation, the spacing ofthe disks 102, and the flow of fluid through the exhaust apertures 105.The gas velocity is preferably kept below sonic speed of about 340meters per second. Larger disk diameters will consequently rotate atslower speeds of rotation. Balancing of the disks 102 is advantageousfor operation at high speeds and increases the longevity and performanceof the turbine.

Boundary layer theory dictates that the viscosity and adhesionproperties of the operating fluid cause the fluid molecules to adhere tothe smooth disk surfaces in the boundary layer at the body surface. Insome embodiments, the disks are spaced to reduce or limit the amount offluid escaping between adjacent boundary layers. In some embodiments,the volume of fluid passing between the disks consists substantially ofonly the sum of the volume of fluid in the adjacent laminar flowboundary layers. For this reason, it is desirable in some embodimentsfor the fluid to flow in a laminar path upon entering the space betweenthe disks, and embodiments provided herein are directed to facilitatethe creation of laminar flow boundary layers that improve or maximizethe operational efficiency of the boundary layer turbine.

For example, in some embodiments, such as in some embodiments ofboundary layer effect compressors, the disks are spaced along the shaftat a distance equal to about twice the width of the boundary layer. Inthese configurations, the boundary layer of each disk does notsubstantially interfere with the boundary layer of adjacent disks, andthe distance between the boundary layers limits the flow of turbulent orfree-flowing fluid between the disks. This facilitates in maximizing,increasing, or improving the transfer of kinetic energy between thedisks and the operating fluid.

As depicted in FIG. 2, laminar, or smooth, fluid flow across the surfacepreserves the shear stresses that create drag forces along the bodysurface and that provide an efficient transfer of the kinetic energybetween the body surface and the fluid. However, turbulent flow acrossthe body surface disturbs the shear stresses and reduces the efficiencyof the kinetic energy transfer, resulting in what is referred to as a“slip condition.” A “no slip condition” occurs where the fluid flow andthe surface has a reduced or substantially no relative motion to oneanother, and which is a goal of some embodiments of the presentdisclosure. This disclosure provides embodiments that facilitate theoperation of the disks 102 as positive displacement entities at highspeeds, but without any mechanical bonding between fluid and surface.Under such conditions, the combined displacement volume of the spacesbetween disks 102 becomes predictable.

This boundary layer effect turbine has an extremely favorablehorsepower-to-weight ratio when compared to any other internalcombustion or turbine engines of comparable output. It also provides ahigh speed electric generator that can be configured to be coupleddirectly to a common shaft with the turbine, thus obviating expensivegear boxes. This disclosure further provides a boundary layer effectturbine that lends itself to scale-ups that may range from about 50 kWeto more than about 2000 kWe power outputs. In some embodiments, theboundary layer effect turbine disclosed herein can also generateenergies below about 50 kWe or greater than about 2000 kWe.

With reference to FIG. 3, a block diagram is illustrated that depictsembodiments of boundary layer effect turbines 200 described herein. Thearrows of FIG. 3 depict the flow of the operating fluid as it passesthrough the boundary layer effect turbine 200. Illustrated in FIG. 3 isa starter or generator 205 that is coupled to a compressor 210. In someembodiments, the coupling between the starter or generator 205 and thecompressor 210 can be through the shaft 110 of the turbine, and thecoupling can include a magnetic coupling. This coupling can reduceinefficiencies in the turbine 200 that may be caused by some mechanicalcouplings.

As depicted in FIG. 3, the compressor 210 can include a cold foginjection 215 for treating operating fluid introduced from an inletprior to compression by the compressor 210. Some embodiments employ acold water cooling system to cool the starter generator 205 and toreduce the air inlet temperature into the compressor 210 for greaterefficiency. The compressor 210 can include a reverse-boundary layereffect turbine disk assembly, as described below, which includes aplurality of disks 102 that operate in reverse fashion to that of theboundary layer effect turbine impellers. In some embodiments, thecompressor 210 can compress the operating fluid in a plurality serial ofstages. As described herein, the compressor 210 is preferably operatedby rotation of the shaft 110, which passes through the compressor 210.In some embodiments, the reverse-boundary layer effect turbinecompressor 210 can be driven by rotation of the shaft 110.

A recuperator 220 is provided in line with the compressor 210 to utilizeexhaust heat from spent operating fluid, or exhaust, by preheating theoperating fluid before the operating fluid passes through a combustor225 or solid oxide fuel cell. In some embodiments, the recuperator 220can provide a crossing flow path of incoming fluid, or fluid coming fromthe compressor 210, and outgoing fluid, or spent fluid to transferenergy from the spent fluid to the incoming fluid. In some embodiments,the recuperator 220 can provide a double cross flow path, in which theincoming fluid crosses paths, through different channels or pathways,with the outgoing fluid twice while flowing through the recuperator 220.This double counter (cross) flow path can enhance the transfer of energybetween the outgoing fluid and the incoming fluid, and can increase theoperation efficiency of the turbine 200 by preheating the incoming fluidprior to the combustion stage.

The fluid is introduced into the combustor 225, or solid oxide fuelcell, to provide heat to the operating fluid. In some embodiments, thecombustor 225 includes a plurality of venturi burners with an adjustableair bypass control ring. The combustor 225 preferably operates to mixfuel, or some combustible content, with the operating fluid, and toignite the fuel to input energy into the operating fluid.

From the combustor 225 or solid oxide fuel cell, the hot operating fluidis directed through a nozzle directed into a turbine expander 230. Thepressurized and heated operating fluid is introduced into the turbineexpander 230 along a perimeter of a disk assembly 100 that includes aplurality of boundary layer effect turbine disks 102. The fluid isdirected substantially tangentially in the turbine expander 230 in avortical flow path from an outer periphery of the disks 102, between thespace between the disks 102, and through an exhaust port 105 toward thecenter of the disks 102. As the fluid flows in the vortical path alongfaces 115 of the disks 102, the fluid drives the disk assembly 100 andtransfers kinetic energy to the disk assembly 100, generating a torque,or moment, about the central axis 125 of the shaft 110 extending throughthe turbine expander 230. The torque causes the disk assembly 100 andshaft 110, which is coupled with the disk assembly 100, to rotate.

The operating fluid is directed from the exhaust port 105 in the turbineexpander 230 back into the recuperator 220. The recuperator 220 directsthe flow of the exhaust fluid to cross paths with incoming fluid thathas been compressed by the compressor 210. The recuperator 220preferably separates the flow of the exhaust flow and the incoming fluidby a plurality of thin walls that are configured to conduct heat fromfluid on one side to fluid on the opposite side of the wall. Asdiscussed above, and shown below with reference to the recuperator 220,the recuperator 220 can provide a double cross-flow path that enhancesthe heat transfer from the exhaust fluid to the incoming fluid. Afterpassing through the recuperator 220, the exhaust fluid is dischargedfrom the turbine 200. Although not depicted in FIG. 3, the exhaust fluidcan then be used from other applications. For example, the exhaust fluidcan then be used for space heating, process heating, or steam generationfor further power generation and/or heating ventilation and airconditioning (HVAC).

FIG. 4 illustrates side, front, and rear views of embodiments of anassembled boundary layer effect turbine 200 having seven sections: aninlet section 250, a compression section 260, a recuperator section 270,a combustion section 280, a turbine expansion section 290, an exhaustsection 295, and a speed reducer section 298.

FIG. 5A is a partial cross-sectional view of the boundary layer effectturbine 200, showing embodiments of the seven sections. A shaft 110extending through the boundary layer effect turbine 200 defines an axis125 of the turbine 200. One end of the shaft 110 is positioned in theinlet section 250. As depicted, the shaft 110 is supported by one ormore bearings 300, which are magnetic bearings in the illustratedembodiments, and is coupled to a starter motor or generator 205.

In some high-speed embodiments, the central shaft 110 can be supportedby at least one magnetic bearing 300, and in some embodiments, thecentral shaft 110 is supported by at least one air bearing 300. In someembodiments, the shaft 110 may be supported by roller bearings 300. Theturbine 200 can be fitted with airfoil or magnetic bearings 300 tofacilitate operation and improve efficiency. Although embodiments ofboundary layer effect turbines 200 can operate with mechanical rollerbearings 300, operation with mechanical roller bearings 300 can increasemaintenance and decrease both longevity of the turbine and efficiency,while limiting the rotating speed of the shaft to the capacity of thebearing 300.

Magnetic bearings 300 used in embodiments of boundary layer effectturbines 200 can be operated by permanent or electric magnets. In someembodiments, the electric magnets are powered by the turbine 200 duringoperation. Additionally or alternatively, the turbine 200 can include atleast one air foil bearing 300. Air foil bearings 300 operate with thepressurized fluid flowing through the turbine 200 and can increaseefficiency and operational longevity of the turbine, without limitingthe rotating speed of the turbine 200. With magnetic and air bearings300, the turbine 200 can be constructed with substantially only onemoving part, the shaft 110, extending through the magnetic bearing 300and the air foil bearing 300. This construction can decrease maintenancerequirements and improve operational efficiency.

The shaft 110 extends through the compressor section 260, where twocompressor assemblies 305, or compressor impellers, are depicted in FIG.5A and are coupled to and driven by rotation of the shaft 110. In someembodiments, the compressor 210 can have one compressor assembly 305, orcompressor impeller, or more than two compressor assemblies 305, orcompressor impellers. The shaft 110 further extends through therecuperator section 270, which includes an air foil bearing 300 aboutthe shaft 110. The shaft 110 extends into the turbine expander 230,where it is coupled to one or more turbine expander assemblies 310, orturbine impellers.

FIG. 5B illustrates a partial cross-sectional view of embodiments of theboundary layer effect turbine 200. The shaft 110 extends from the speedreducer 298, through the starter 205, and into the compressor section260. In some embodiments, the recuperator section 270 and the turbineexpander 230 can be modified from that depicted in FIG. 5A. In FIG. 5B,the recuperator section 270 is shown as having a plurality of pathwaysleading to multiple combustors 280. Additionally, the recuperatorsection 270, in some embodiments, can have a plurality of exhaustoutlets 295. Four combustors and/or four outlets are more efficient thanone large burner, as it allows for a more even tangential entry of theoperating fluid into the turbine expander 230.

FIG. 6A is a partial side view of the boundary layer effect turbine 200further isolating components of sections separated from the respectivesection housing. Depicted in FIG. 6A is the shaft 110 that extends fromthe inlet section 250, through the compressor section 260 andrecuperator section 270, and into the turbine expander section 290. Insome embodiments, the shaft 110 can be a unitary component that isintegrally formed and extends through all sections of the turbine 200.In some embodiments, the shaft 110 can be manufactured in separateportions and can be interlinked or coupled during assembly of theturbine 200. In some embodiments, the coupling of the shaft 110 can bean interlocking configuration of mating ends of the shaft 110, and insome embodiments, the shaft 110 can be coupled by magnetic couplings.

FIG. 6B depicts some embodiments of the turbine 200 with embodiments offluid paths through the turbine 200. The fluid enters into thecompressor section 260 from the left. The compressor assembly 305, orrotating disks in a rotor-stator cavity, creates a radial outflow offluid within the boundary layer along the disks 102. In someembodiments, as depicted in FIG. 6B, the compressor section 260 can haverepeated portions that compress the fluid before introducing the fluidinto the recuperator section 270 to receive heating from the exhaust ofthe turbine expander section 290.

The compressor section 260 can include expanded portions that functionas a diffuser to allow the fluid to decrease velocity and increasepressure. The compressed fluid can be scavenged, or drawn, from thediffuser, or expanded portion, into a second stage, where the diskassemblies 305 are configured to have thicker protrusions, or spacers,between the disks 102. As discussed in more detail later, these spacers,or blades, are shaped to present a larger cavity at the center of thedisk 102 that at the periphery, to reduce any pinching effect that couldcreate a drop in pressure. The larger cavities between the disks 102 ofthe assembly 305 can permit the fluid to move freely toward the centerof the disk 102 to counteract the centrifugal force imposed by therotating disk 102, which could contribute to a stalling condition.

In a third compressor 210 stage, the fluid is directed outward again ina similar manner as in the first stage. The compressed fluid is thendirected into a plurality of thin-walled tubes of the recuperatorsection 270 to receive heat from cross-flowing heated fluid. After beingpreheated by the cross-flowing heated fluid, the operating fluid isdirected into at least one or more combustion sections 280, where thefluid is further heated by a combustor 225 before being introduced intothe turbine expander section 290. After the fluid is expanded in theturbine expander section 290, the fluid is directed through therecuperator section 270 to preheat incoming compressed fluid from thecompressor section 260 through a double cross-flow path. Afterpreheating the cooler compressed fluid, the exhaust fluid is thendirected through exhaust ports 295.

Illustrated in FIG. 7 are embodiments of a compressor 210 having twocompressor impellers 305 in series. In some embodiments, the compressor210 operates in reverse to the methods of the turbine impellers 310. Forexample, in some embodiments, the compressor 210 includes a plurality ofboundary layer effect turbine disks 102 that are driven to move theoperating fluid.

Although FIG. 7 illustrates the compressor 210 as having two compressorimpellers 305, with the same diameters, in series to compress the fluid,other constructions of the compressor 210 are contemplated in thisdisclosure. For example, the compressor 210 could be configured with asingle compressor impeller 305. In some embodiments, the compressor caninclude more than two compressor impellers 305.

In some embodiments, although not depicted in FIG. 7, the compressor 210can include compressor impellers 305 with varying size of disks 102. Forexample, the compressor impeller 305 can include disks 102 that havedifferent diameters. In some embodiments, a compressor impeller 305 hasa plurality of disks 102 that each have increasing diameters as thedisks 102 are assembled along the shaft 110, such that the disks 102 ofthe impeller 305 have an increasing diameter along the fluid path fromthe inlet 350 of the compressor 210 toward the recuperator 220. In someembodiments, a compressor impeller 305 has a plurality of disks 102 thateach have decreasing diameters as the disks 102 are assembled along theshaft 110, such that the disks 102 of the impeller 305 have a decreasingdiameter along the fluid path from the inlet 350 of the compressor 210toward the recuperator 220.

In some embodiments, the diameter of the disks 102 within eachcompressor impeller 305 are the same, but the diameter of eachcompressor impeller 305 is different. For example, a first compressorimpeller 305 can have a first diameter, and a second compressor impeller305 can have a second diameter. In some embodiments, the first diameteris greater than the second diameter, and in some embodiments, the seconddiameter is greater than the first diameter.

The same principle of utilization of the fluid's viscosity and adhesionproperties are implemented to draw the operating fluid through thecompressor 210 by driving the compressor impellers 305. However, whenthe compressor impellers 305 are in operation, the fluid flows into theinlet 350 at a middle portion of the disks 102. In the first compressionchamber 355, or volute, surrounding the first of the two depictedcompressor impellers 305, the working fluid is directed to the center ofthe second compressor impeller 305, as indicated by arrow 358. Theworking fluid passes through the compression fluid inlets 360 of thesecond compressor impeller 305 and is driven to a central entrance ofthe recuperator 220.

In some embodiments, the fluid inlet 350 of the compressor impellers 305have a decreasing volume along the flow path of the operating fluid. Insome embodiments, the decreasing volume directs the fluid from thecompressor inlet 350 to spaces between the compressor disks 102. In someembodiments, the decreasing volume is, in part, created by asemi-frustoconical member 365 within the compressor impeller inlet 350.The member 365 can include one or a plurality of vanes 366 (FIG. 8A)that direct fluid into the inlet 350 and through spaces between thecompressor disks 102. In some embodiments, the member 365 enhances theequal distribution of fluid through the spaces between the disks 102.

Embodiments of the boundary layer compressors 210 described herein canbe used in conjunction with the boundary layer turbine 200, or can beused for other purposes that are independent of the turbine 200. Forexample, the compressors 210 are suitable as small lightweightcompressors and as very large industrial compressors for newapplications, such as carbon dioxide compression for subsequentunderground sequestering in aquifers. These embodiments describe newhigh efficiency gas compressors that operate at high speed, in whichimproved compression performance and functional durability are attainedby the use of boundary layer principles, which, as described elsewhereherein, utilize the adhesive and viscosity properties of gaseous fluidsemployed, combined with specially shaped spacers to provide efficientcompression of said fluids. Compressors so constructed are particularlyuseful for compression of air, carbon dioxide, refrigerants, steam,hydrocarbons, and other compressible fluids in either freestanding modeor as integrated elements of turbo-machinery.

Described herein are embodiments of simple, highly efficient andinexpensive gas compressors 210 for a wide variety of gas compressionapplications. Gas compression uses considerable amounts of energy, andapplications and embodiments of the compressors described herein canprovide significant efficiency improvements over other designs. In thecase of microturbines, it has been found that in some designs, thecompressor section 260 can use more than about 50% of the gross powerdeveloped by the turbine. The embodiments of compressors 210 describedherein offer increased efficiency, reduced operating costs, reducedfirst cost for the equipment, reduced maintenance costs, and are able tooperate at very high shaft 110 speeds so as to be able to operate offthe same shaft 110 as a turbine 200 without the use of a gear box.

In particular, several distributed power generators, powered bymicroturbines, demand a much greater level of overall efficiency inorder to compete with grid power. The application of microturbines forautomotive and marine craft application can benefit from a compactcompressor capable of operating at rotating speeds in the range of20,000 to 150,000 rpm, which are the normal operating speeds ofmicroturbines. The important advantages of the gas compressors describedherein can be employed for micro turbine applications as well as formajor industrial scale applications, and the myriad of sizes between.

Illustrated in FIGS. 8A-8K are embodiments of impellers 305, 310, e.g.,for fluid compressors 210, such as gas compressors, based on the use ofa driven impeller 305, 310 consisting of a plurality of flat disks 102,spaced apart by spacers 420 that can also act as flow resistanceelements to guide the fluid, or gas, flow between disks 102 into apredetermined flow path to enhance energy transfer between the fluid andthe disks 102. The impeller 305, or rotor, of the boundary layer effectcompressor 210 drives the disks 102, which moves the operating fluid ina radially vortical path through narrow spaces between the disks 102.The fluid is driven by adhesion of the fluid to the surface, or face115, of the disks 102, e.g., in the boundary layer, as well as beingdriven by the spacers 420, which function similar to vanes to positivelydisplace the fluid. Embodiments of the compressors described herein canmove large quantities of fluids at relatively low pressure ratios andare, apart from air compression, also effective in compressing heaviergases such as carbon dioxide, ammonia or methane.

FIG. 8A depicts a front view of embodiments of the compressor impeller305 with a bold arrow 405 depicting that rotation of the impeller 305 isin the clockwise direction and a smaller arrow 410 depicting thedirection of air flow as a consequence of rotation of the compressorimpeller 305. In some embodiments, the compressor impeller 305 includesa center vane section 415 oriented immediately around the shaft 110 asit extends through the impeller 305, as mentioned above with respect toFIG. 7. Ambient air is drawn into the center vane section 415 andallowed to disperse in the voids between the axially spaced disks 102.

In some embodiments, the spacers 420 of the compressor disks 102 includeone or more, or at least one, elevated vane 420, as shown in FIG. 8A, onthe face 115 of the disk 102 to further capture and move the workingfluid along the disk face 115. The vanes 420 can, in some embodiments beformed in an aerofoil shape so as to limit disturbance of laminar flowof the working fluid along the face 115 of the disk 102. As the impeller305 rotates, the elevated vanes 420 drive the working fluid to the outeredge 120 of the compressor impeller 305, where the fluid is compressedand directed to the next section of the boundary layer effect turbine200.

Aerofoil sections can be used in centrifugal rotors, such as in vanepumps and compressors, and the aerofoil sections can be integrallyformed on the disk 102 or affixed to the disk 102 through two or morelocating holes 425 to obviate welding spacers to the disks. Althoughsome embodiments of the present disclosure are configured to accommodateaerofoil sections that are welded, some embodiments are configuredwithout welding, as welding can create stress raisers that can cause thedisks to fail because of the forces involved when the impeller 305 spinsat speeds from about 20,000 rpm to about 100,000 rpm. Utilization ofonly one fixing point without welding can cause the spacer 420 to swingopen at high temperatures and under full load conditions should thedisks 102 start to expand or distort. In some embodiments, washer shapedspacers can be used to separate the disks 102.

In some embodiments, ambient air is drawn around the starter/generatorinto the inlet vanes 365 at the inlet port 350 of the compressor 210 anddistributed evenly into the narrow spaces between the disks 102, causingair to move radially outwards in an outward spiral, to be discharged atthe periphery into a diffuser 430 where the velocity is reduced causingthe gas to present at higher pressures than ambient. The air is thendirected to the inlet of a second compressor and is compressed asdiscussed above. Upon discharge of the air into a second diffuser, theair is then directed to an inlet of a recuperator 220.

FIG. 8B illustrates another embodiment of the compressor impeller 305with a bold arrow 460 depicting rotation of the impeller 305 in thecounter-clockwise direction. In this embodiment, the elevated vanes 420extend from a point near or at the inner edge 465 of the disks 102 to apoint near or at the outer edge 120 of the disks 102. In someembodiments, the compressor impeller 305 can have a first plurality ofdisks that operate to direct fluid from the inner edge 465 of the disks102 to the outer edge 120 of the disks 102 and a second plurality ofdisks 102 that operate to direct fluid from the outer edge 120 of thedisks to the inner edge 465 of the disks. In some embodiments, the firstand second plurality of disks 102 can be separated by a central disk,which also operates to separate the fluid inlet from the fluid outlet.

In some embodiments, the compressor impeller 305 can have a firstplurality of disks 470 that operate to direct fluid from the inner edge465 of the disks 102 to the outer edge 120 of the disks 102 and a secondplurality of disks 480 that operate to direct fluid from the outer edge120 of the disks 102 to the inner edge 465 of the disks 102. In someembodiments, the first and second plurality of disks 470, 480 can beseparated by a central disk 490, which also operates to separate thefluid inlet 350 from a fluid outlet 352, as shown in FIG. 8C.

Certain embodiments include a plurality of disk stacks 470, 480, onestack 470 forming a first phase 510 of the compressor 210, the secondstack 480 comprising a second phase 520 of the compressor 210, bothstacks 470, 480 being mounted on a common shaft 110 with a sturdydividing disk, or central disk 290, between the stacks 470, 480 and ontowhich fixing pins 525, which hold the disks 102 together as a singlecomposite stack, are affixed.

In some embodiments, the disks 102 have elevated vanes 420, in of thefirst phase 510, that have widths that extend from an inner regionadjacent the interior edge 465 of the disk 102, which is located nearthe rotation axis 530, about which the disks 102 rotate, to a regionadjacent the outer edge 120 of the blade member 102. In someembodiments, the blade member, spacer blade, or elevated vane 420, iscurved along its width so as to gently drive the fluid along a leadingedge 461 from the inner region adjacent the interior edge 465 toward theouter edge 120 of the disk 102.

In some embodiments, the curvature of the spacer blades 420 mountedbetween the disks 102 of the second phase 520 face in the oppositedirection as the spacers 420 of the first phase 510, acting, when theshaft 110 is rotated, to drive the fluid towards the shaft 110 in adecreasing space to further increase its pressure.

In some embodiments, the member 365, or central boss, which extendsaxially along the rotor or shaft 110 from the central dividing disk 490,is shaped to compensate for the reducing volume of gaseous fluidentering the central stacks of the first phase 510. For example, asdepicted in FIGS. 8C and 8F, the central boss, or axially extendingmember 365 can be concave with an increasing radial dimension as themember 365 is closer to the central disk 490, and thus reduces thevolume between the inner edge 465 of the disks as the fluid is drawncloser to the central dividing disk 490. Similarly, the central boss 365of the central dividing disk 490 is also shaped in the second phase tocompensate for the increasing volume of gaseous fluid, which fluidleaves the disks 102 via the cylindrical space around the shaft 110.

For example, FIG. 8C illustrates an embodiment of a compressor impeller305 with a first plurality of disks 470 that move fluid from the fluidinlet 350, along the shaft or rotor 110 of the compressor 210, betweenthe disks 102 to a diffuser 430. A second plurality of disks 480 of thecompressor impeller 305 operate to move the fluid from the diffuser 430toward the center of the disks and toward a fluid outlet 352. Tofacilitate flow of the fluid through the diffuser 430 and into the spacebetween the second plurality of disks 480, the impeller 305 may includea plurality of radially extending diffuser vanes 540 that extend from aposition near or at the outer edge 120 of at least one of the disks 102into the diffuser 430.

The diffuser vanes 540 are preferably configured to move fluid throughthe diffuser 430, from the first plurality of disks 470, to the secondplurality of disks 480. In some embodiments, the diffuser vanes 540 areconfigured to direct the movement of air from the diffuser 430 towardthe second plurality of disks 480. In some embodiments, the diffuservanes 540 extends radially from the compressor impeller 305, and in someembodiments, the diffuser vanes 540 are coupled to the central disk 490.

In some embodiments, the diffuser vanes 540 are configured to bestationary with respect to the rotating disks 102. For example, thediffuser vanes 540 can extend into the diffuser volume from thecompressor housing 359 (FIG. 7), thus impeding the rotational spin ofthe fluid, and guiding the fluid to a second portion of the diffuser430. In these embodiments, the velocity of the fluid is decreased, thusconverting the kinetic energy of the fluid into pressure and allowingthe air in the second portion of the diffuser to be directed into thesecond plurality of disks 480.

As depicted in FIG. 8D, the second plurality of disks 480 may beslightly modified from that of the first plurality of disks 470illustrated in FIG. 8B. In some embodiments, the compressor impellerrotates in the counter-clockwise direction as indicated by a bold arrow545. In these embodiments, the elevated vanes 420 can extend from apoint near or at the inner edge 465 of the disks 102 to a point near orat the outer edge 120 of the disks 102. However, in some embodiments, acurvature of the elevated vanes 420 of the second plurality of disks 480can be substantially opposite a curvature of the elevated vanes 420 ofthe first plurality of disks 470. In some embodiments, the curvature mayvary between the first and second plurality of disks 470, 480.

For example, a leading edge 461 of the elevated vanes 420 of the firstplurality of disks 470, as illustrated in FIG. 8B is depicted as havinga convex curvature. In some embodiments, a leading edge 550 of theelevated vanes 420 of the second plurality of disks 480, as illustratedin FIG. 8D is depicted as having a concave curvature. Alteration of thecurvature between the first and second plurality of disks 470, 480 canserve to facilitate flow of the fluid through the compressor 210. Forexample, the concave curvature of the elevated vane's 420 leading edge550, as depicted in FIG. 8D, can function to draw fluid into theplurality of disks and direct the flow of fluid toward the center of thedisks and toward the fluid outlet 352.

In some embodiments, at least one of the arcuate elevations, spacers, orelevated vanes 420, comprises a different material than does at leastone of the disks 102. The selection of materials and the mechanicaldesign of rotating components in the embodiments envisioned herein limitor reduce use of excessive quantities or weights of materials, but thedesign provides the strength where desired in the rotor, commensuratewith the centrifugal forces acting on the rotating components.

FIG. 8E depicts a rear view of some embodiments of the compressorimpeller 305. In these embodiments, the diffuser vanes 540 are depictedas extending into the diffuser 430 from a location near or at the outeredge 120 of the first or second plurality of disks 470, 480, and theelevated vanes 420 on the face 115 of the disks 102 are illustrated asextending from the outer edge 120 of the disk 102 to the inner edge 465of the disk 102.

In some embodiments, as illustrated in FIGS. 7 and 8F, more than onestage of the compressor can be employed, with the gaseous fluid flowingfrom one compressing stage to the next, undergoing multiple distincttreatments to increase pressure of the fluid. For instance, in someembodiments, the fluid, or gas, will first be drawn axially into theinlet 350 at a center of the compressor 210 and directed radiallyoutward by centrifugal force and rotation of the disks 102. In someembodiments, the speed, or velocity, of the fluid can approach nearsonic speed upon being discharged from the outer edges 120 of the disks102. The fluid is then allowed to slow down in a circumferentialdiffuser 430 presenting an increased volume. To occupy that volume, thefluid slows down, converting speed into pressure.

In some embodiments, the diffuser 430 is shaped in such a way that thefluid is re-injected tangentially into the spaces between the disks 102,where it is driven radially inward mostly by the reaction force againstthe spacers 102, which act as vanes to direct the fluid toward thecentral outlet port 352. The diffuser vanes 540 in the diffuser 430change the direction of the moving fluid from one phase to the next and,in some embodiments, further slows down the moving fluid to allow theaerofoil spacers 420 to draw in the fluid, or gas, and to drive itinwards. Centrifugal force counteracts the movement of the fluidinwards, thus increasing the pressure of the fluid, with centrifugalforce acting radially outwards and with positive displacement force actsinwards. Simultaneously, the fluid passes through a decreasing volume,which further increases the pressure. In some embodiments, to avoid astalling situation, the spaces between the second plurality of disks480, or second phase of disks 520, are larger than the spaces betweenthe first plurality of disks 470, or first phase of disks 510, causingthe gaseous fluid to travel more freely through the turbulent zone,somewhat away from the laminar flow zone (as shown in FIG. 17B). Third,fourth, and further additional stages can be added in series accordingto the desired pressure ratios.

FIG. 8F depicts a plurality of compressor impellers arranged in seriesfor providing sequential compression of the fluid. Not depicted in FIG.8F are the diffuser vanes 540, although some embodiments of compressors210, having a plurality of compressor impellers 305, also includediffuser vanes 540. The arrows in FIG. 8F depict the flow path of thefluid as it travels through multiple stages of the compressor 210.

FIGS. 8G and 8H depict embodiments of compressors 210 that areconfigured to direct the operating fluid to an outer periphery of therecuperator 220 instead of through a central portion, as depicted, forexample, in FIG. 8F. In some embodiments, the fluid follows a similarpath through the compressor 210 as described with other embodiments, andis directed to the recuperator through an outlet 352 that can include,for example, a plurality of tubes circumferentially arranged around therecuperator 220 to direct flow of the compressed fluid. In someembodiments, the outlet 352 can include an annular passageway that isopen to the diffuser 430, as illustrated in FIG. 8H.

In some embodiments, the shape of the elevated vanes 420 can be adjustedto align closely with the flow of fluid through the compressor 210 whenthe turbine 200 is operating under normal operating conditions. In someembodiments, adjustments to the vanes can be made to slightly impose adisplacement force on the fluid flowing past the vanes 420.

Depicted in FIG. 8I is one embodiment of a method of determining thealignment of the vanes 420. FIG. 8I shows the flow of fluid along a disksimilar to that used in embodiments of the turbine 200. A first radius Bcorresponds to an inner disk radius, and a second radius A correspondsto an outer disk radius. The white fluid lines illustrate the naturalflow of fluid as it is acted upon by a face of the disk. Solid line 531corresponds to the natural flow of fluid, and dashed line 533corresponds to an exemplary alignment of the elevated vane 420 that willfurther act upon the fluid with a displacement force.

Some embodiments of a method of aligning the vanes 420 includesidentifying an unimpeded flow of fluid over a disk 102 of the turbine200 at normal operating conditions and identifying a desired alignmentof an edge of a vane 420 that will impose a displacement force upon thefluid. In some embodiments, the method can further include adjusting thevane 420 to the desired alignment. In some embodiments, these methodsare used to adjust the vanes 420 in at least one of the compressor 210and the turbine expander 230.

FIGS. 8J and 8K depict various embodiments of elevated vanes 420 inconnection with, for example, embodiments of the compressor 210. FIG. 8Jdepicts a front axial view of an embodiment of the compressor 210,showing a disk 102 and elevated vanes 420 arranged to move fluid to anouter periphery of the disk 102. FIG. 8K depicts a rear axial view of anembodiment of the compressor 210, showing how the rear elevated vanes420 can be configured to increase the flow area along the disk from theouter periphery of the disk toward the inner portion of the disk 102. Insome embodiments, a relative size of the outlet port 352 on theperiphery can be about 300% larger than the inlet ports 350 at thecenter, to allow the fluid to increase its pressure by occupying agreater volume. In some embodiments, the outlet ports 352 in the centerof the disks 102 are about 130% of the inlet ports 350 at the periphery.

Some embodiments include a gas bypass arrangement, which can permit partof the compressed gas output between phases or stages to be vented asdesired, while maintaining high rotating velocity when utilizing thecompressor drive apparatus and while maintaining minimal output loads.

Parameters that can determine the performance characteristics of a diskturbine design, for example, a two stage disk turbine design, include adiameter of compressor and turbine disks 102, the rotor speed, the gapsbetween the disks 102, the number of disks 102, the shape of theelevated spacers 420, and the inlet nozzle (directing fluid into theturbine expander 230) design. Embodiments described herein providetheoretical and empirical parameters that are configured to optimizeoperational performance of the boundary layer effect turbine.

In some embodiments, the compressor 210 includes compressor disks 102having a diameter of about 25 cm. In some embodiments, the compressor210 can have disks 102 with diameters ranging from about 20 cm to about30 cm. Some embodiments include compressors 210 with disks 102 havingdiameters ranging from about 15 cm to about 35 cm, and some embodimentsinclude compressors 210 with disks 102 having diameters less than about15 cm or greater than about 35 cm.

In some embodiments, a compressor impeller 305 can include about 24disks 102. In some embodiments the compressor impeller 305 can have fromabout 18 disks 102 to about 30 disks 102, and in some embodiments, thecompressor impeller 305 can have from about 12 disks 102 to about 36disks 102. In some embodiments, the compressor impeller 305 can haveless than about 12 disks 102 or greater than about 36 disks 102.

In some embodiments, the number of compressor disks is dependent uponthe number of turbine disks, or the number of compressor disks isdetermined by a ratio with respect to the turbine disks. For example, insome embodiments the ratio of compressor disks to turbine expander disksis about 2.5:1. In some embodiments, the ratio ranges from about 2.3 andabout 2.7 compressor disks to each turbine expander disk, and in someembodiments, the ratio ranges from about 2.0 and about 3.0 compressordisks to each turbine expander disk. In some embodiments, the ratio isless than about 2.0 or greater than about 3.0 compressor disks to eachturbine expander disk. For example, in some embodiments, the ratio isabout 3.5, about 4.0, about 5.0, about 7.5, and about 10.0 compressordisks to each turbine expander disk.

In some embodiments, the rotational speed of the compressor 210 is thesame as that of the shaft 110, as driven by the turbine expander disks102. In some embodiments, the rotational speed of the compressor isabout 20,000 rpm. In some embodiments, the rotational speed of thecompressor ranges between about 15,000 rpm and about 25,000 rpm. In someembodiments, the rotational speed of the compressor ranges from about10,000 rpm to about 30,000 rpm. In some embodiments, the rotationalspeed of the compressor is less than about 10,000 rpm or greater thanabout 30,000 rpm. For example, in some embodiments, the rotational speedof the compressor can be about 40,000 rpm, about 50,000 rpm, about75,000 rpm, and about 100,000 rpm. In some embodiments, the rotationalspeed of the compressor can be variable depending on the desired outputof the turbine 200.

In some embodiments, the compressor disks 102 are spaced at a distanceto enhance the efficiency of the compressor 210. In some embodiments,the compressor disks are spaced about 1.2 mm apart. In some embodiments,the compressor disks are spaced between about 1.1 mm and about 1.3 mmapart, and in some embodiments, the compressor disks are spaced betweenabout 1.0 mm and about 1.4 mm apart. In some embodiments, the compressordisks are spaced less than about 1.0 mm or greater than about 1.4 mmapart. In some embodiments, the compressor disks are spaced a variousdistances apart depending on the desired flow characteristics throughthat portion of the compressor 210.

This disclosure provides further improvements on management of theoperating fluid to reduce inherent losses as the fluid flow enters andexits the rotor, or impeller 305. In some embodiments, the inlet andexhaust ports 350, 352 or apertures 105 are configured to be asubstantially annular shape concentrically oriented about the shaft 110,as illustrated in FIGS. 8A-8H. Alteration of the inlet and exhaustapertures to an annular passageway, which forms an annular channel whena plurality of disks are assembled, reduces flow restrictions of thefluid during operation and increases efficiency of flow through thecompressor and expander. In FIGS. 8A-8H, the disks 102 are affixedaround a set of vanes 366, with the vanes 366 offering an unobstructedinlet or outlet port of the impeller 305, making possible a streamlinedand continuous spiral flow of the fluid.

In some embodiments, the disks 102 used in the impellers 305 have across-sectional profile with flat and abrupt outer edges, as depicted inFIG. 9A. While the boundary layer effect turbine 200 is operational withsuch disks 102, these disks 102 can increase the creation of turbulentflow through the impellers, creating eddies and decreasing operationefficiency of the turbine.

In some embodiments, as depicted in FIG. 9B, the outer edge 120 of thedisks 120 can have a streamlined cross-sectional profile that enhancesthe flow of laminar flow over the surface of the disk. As depicted, thedisks 102 can have tapered edges that resemble the front of an airfoil.This shape enhances the flow of laminar flow between the disks 102 asthe fluid is guided through the impellers 305. As reflected in thefigures, the disk 102 has an edge portion in which, moving inward froman edge 120 of the disk 102, a cross-sectional thickness of the diskincreases at a decreasing rate along an edge portion length. In someembodiments, as shown in FIG. 9C, the disks can have a streamlinedinterior portion along the inner edge 465 where the exhaust aperture islocated in addition to the streamlined portion along the outer edge 120of the disk 102.

The streamlined edges of the disks 102 allow the fluid to flow morefreely between the narrow spaces between the disks 102 in a laminar flowpattern, thus imparting the molecular energy of the fluid to the disksurface and reducing slippage between the fluid and the disk surface asa consequence of turbulent flow. The boundary layer effect turbine 200described in this disclosure enables the fast-moving fluid to transfermore gently into and out of the impellers 305, thus avoiding turbulentflow and yielding higher efficiencies.

FIG. 10 shows embodiments of the assembly of a boundary layer effectturbine 200 for generating power with arrows depicting the path of theoperating fluid through portions of the stages shown. Illustrated arethree stages, namely the compressor 210, recuperator 220, and theturbine expander 230. The operating fluid is compressed in thecompressor 210, preheated in the recuperator 220, introduced into thecombustion chamber 230, and mixed with the hot gases from the burners.The hot and pressurized gas is then introduced into the turbineexpander.

After expanding the hot fluid via the expander 230 and turbine impeller,the spent gas is discharged into the recuperator 220 to preheat incomingcompressed fluid and is then discharged via a tangential exhaust 235 andmay then be used as an oil free heating medium for other applications.FIGS. 11, and 12A-12G illustrate embodiments of the recuperator 220. Asfluid enters the recuperator 220 from the turbine expander 230, it flowsaround a concentric passage 620 around a bearing capsule 630. The fluidenters a plenum chamber 640 from whence it is distributed into aplurality of small diameter, thin-walled, creep-resistant stainlesssteel tubes 650, such as of grade 321. The voids between the stainlesssteel tubes 650 are preferably filled with long fiber stainless steelwool 660, that presents a low-pressure drop to the compressed airpassing through it, while increasing the effective surface area. In someembodiments, this stainless steel finned plates are provided to transferenergy.

Compressed air enters a first concentric passage 660, from thecompressor 210, and flows around the bearing capsule 630, flowingtowards the hot side in a counter flow mode. This flow keeps the bearingcapsule 630 cool, and the compressed fluid starts to accept heat fromthe hot outer passage 620 before the fluid is distributed to the voidsbetween the tubes 650 by means of a multitude of inlet ducts 665. Thecompressed air is allowed to travel, in a second cross-flow path, at areduced speed through the stainless steel wool 660, or other transfermedium, around the tubes 650, allowing for ample time to absorb the heatfrom the thin walled tubes 650. It is conservatively estimated that therecuperator 220 can recover more than about 80% of the heat from thecounter flowing exhaust gas. In some embodiments, the recuperator 220recovers between about 70% and about 90% of the heat from the counterflowing exhaust gas. In some embodiments, the recuperator recoversgreater than about 90% of the heat from the counter flowing exhaust gas.In some embodiments, the recuperator 220 recovers between less thanabout 70% of the heat from the counter flowing exhaust gas. In someembodiments, the recovery of heat is determined by a change intemperature of both the exhaust and compressed fluid from when the fluidenters the recuperator and the temperature of the fluid leaving therecuperator in the exhaust and the temperature of the fluid leaving therecuperator toward the combustion chamber. In some embodiments, arecovery of 70% corresponds to a 70% reduction in temperature differencebetween the compressed fluid and the exhaust fluid from the time thefluid enters the recuperator until the time the fluid exits therecuperator.

FIGS. 12A-12C depict various views of embodiments of the recuperator220. FIG. 12A shows a perspective view of embodiments of the recuperator220 in which the fluid enters the recuperator in a center portion of therecuperator through the first concentric passage 660. FIG. 12Billustrates a partial cross-sectional schematic view of the recuperator220, showing the first concentric passage 660 that directs fluid throughthe inlet ducts 665 to the interstitial spaces between the tubes 650 andtoward the combustion chamber. Also depicted in FIG. 12B is the outerpassage 620, which conducts exhaust fluid in a first cross-path aroundthe first concentric passage 660, and which is in communication with thetubes 650, through which the exhaust fluid flows in a second cross-pathpast the compressed fluid toward the exhaust outlet port 235. FIG. 12Cdepicts an axial view of embodiments of the recuperator 220, showing thethin walled tubes 650 and the first concentric passage 660. FIGS.12A-12C also depict a central passageway 651, through which the shaft110 can extend and rotate.

FIG. 12D-12F depict embodiments of the recuperator 220 that include aplurality of outlet ports 662 positioned about a periphery of therecuperator 220. Also depicted are inlets, or entry ports 663 about theperiphery of the recuperator 220. FIG. 12D also depicts a dischargemanifold 664 and a return manifold 665 on opposing ends of therecuperator 220. FIGS. 12E-12F depict embodiments of the recuperatorhaving a plurality of exhaust ports 235 positioned around the peripheryof the recuperator 220. FIG. 12F also depicts the recuperator 220 havingthe plurality of outlet ports 662 in communication with a plurality ofcombustors 225.

In some embodiments, as depicted in FIG. 12G, the recuperator 220includes an air foil bearing 668. In some embodiments, the bearing 668is configured to provide support to the shaft 110 during rotation of theshaft 110 and when the turbine 200 is in operation.

FIG. 13A shows embodiments of a turbine expander 230 that has a variantof aerofoil shaped spacers 420 affixed to, or integral with, a disk 102embodied in the turbine expander impeller 700. Hot fluid is injectednearly tangentially and is directed in a circular, vortical path, asindicated by arrow 710. The hot fluid is allowed to expand in the spacesbetween the disks 102. In so doing, the fluid impinges upon the spacers420, imparting its kinetic energy by boundary layer adhesion as well asby reaction force. Leaving the spacers 420, the gas expands to thecenter outlet port 105, releasing further energy via the boundary layereffect to the disk surface and finally to the vanes 730 at the centeroutlet port 105.

In some embodiments, the turbine expander impeller 700, or turbineimpeller 700, includes a plurality of annular disks 102, and each of thedisks have a face 115. The disks 102 are preferably spaced apart from anadjacent disk, such that planes containing the surfaces or faces 115 ofadjacent disks 102 are substantially parallel. In some embodiments, eachdisk 102 has an outer edge 120 and an inner opening 465, through whichthe central shaft 110 extends. As depicted in FIG. 13, the disks 102 areconfigured to transmit kinetic energy between the disks 102, as theyrotate about the shaft 110, and fluid introduced into the turbineexpander 230 through a fluid inlet port 740. The transmission of kineticenergy results, at least in part, from a boundary layer formed at theface 115 of at least one of the disks 102. In some embodiments, eachdisk 102 includes a plurality of elongate, arcuate elevations 420 thatextend along the face 115 of the disk 102.

The arcuate elevations 420 preferably include a first region 750 and asecond region 760. The first region 750 is located closer to the shaft110, or central axis 125 of the shaft 110, than is the second region 760of the same arcuate elevation 420. In some embodiments, the arcuateelevation 420 tapers in width as it extends from the first region 750 tothe second region 760, such that a width of each of the arcuateelevations 420 at its first region 750 is greater than a width of thesame arcuate elevation at its second region 760.

Accordingly, when the disks 102 are being used as a turbine impeller700, as depicted in FIG. 13A, fluid will flow from the turbine expanderinlet 740 toward the outer edge 120 of the turbine impeller 700. As thefluid impinges on the outer edge 120 of the impeller 700, or pluralityof disks 102, the fluid is directed into spaces between the disks 102.As the fluid enters into this region, it is directed radially inwardlytoward the center of the disks 102. The reaction forces of thisdirection causes the disks 102 to apply a torque, or moment, on theshaft 110, which rotates the shaft 110. A torque on the shaft 110 isalso applied by the boundary layer effect caused as the vertical flow offluid travels over the face of the disks 102.

FIG. 13B illustrates embodiments of the turbine expander 230 having aplurality of fluid inlet ports 740. Embodiments with a plurality offluid inlet ports 740 can distribute the working fluid into the turbineexpander 230 more evenly about the turbine impeller 700 than expanders230 having a single inlet port 740. As explained herein, someembodiments have one inlet port 740 and some embodiments have aplurality of inlet ports 740.

As shown in FIG. 14, the turbine impeller 700 is shown with arrowsdepicting the flow of operating fluid into and through the turbineexpander 230. In the turbine expander 230, a pressurized fluid istangentially injected at the circumference, perimeter, or outer edge 120of the disks 102 and dispersed at high pressure and velocity between thedisks 102, moving over the smooth surface in the boundary layer on thesurfaces of every disk 102. The spaces between disks 102 are sized to bethe sum of the two laminar flow regions of the boundary layers, wherethe relative speed between fluid and surface approaches zero. Fluidmolecules are forced in a spiral path between the disks 102, clinging tothe surface to transfer the molecular energy of the hot fluid in ashearing action to the surface. The spent fluid then exits at the centerof the disks 102 through an outlet 770, which is in communication withthe recuperator 220, driving axial vanes 730 of the impeller 700 uponleaving the impeller 700.

The flow of fluid along the surface of the faces 115 of the disks 102combines with the reaction force against the aerofoil spacers 420 andinduces the disks 102 to move with the fluid in accordance with theboundary layer effect described above. When a load is applied, an amountof slip has a tendency to occur without the airfoil shaped spacers 420and has been found to be proportional to the workload. The greater theload, the more direct the route taken by the expanding gas from theouter edge 120 to exit 105, until stalling conditions become manifest.The introduction of aerofoil shaped spacers 420 assists in maintaining aconstant flow pattern to maintain a constant speed and torque and toreduce the amount of slip.

When using circular spacer washers, up to 94% energy conversionefficiency can be achieved in a no load condition, reducing, withincrease load, until a stalled condition is reached. For a well designedexpander 230, the energy conversion efficiency is determined (Btu in thefuel is converted to kWe) by the shape and size of the inlet nozzle 744and thus the velocity of the entering gas. Under no load conditions, thedisk tip speed (or the speed of the outer edge 120 of the disks 102)approaches the fluid velocity, according to boundary layer theory, thegeometry of the inlet and outlet edges 120 of the disks 102, the spacebetween the disks 102, the number and size of the disks 102, the shapeof the spacers 420, and the operating speed of the disk impellers 700and the angle of attack (or orientation) of the aerofoil shaped spacers420.

Although the compressor 210 also uses the boundary layer effectmechanism, a compressor 210 using boundary layer drag theory operatesdifferently from a turbine expander 230. In the case of the compressor210, the driven surfaces move at high speeds over low speed ambient air.Centrifugal force forces the fluid to the edge 120 of the disk 102 andcreates a low pressure region between the disks 102 with the ejection ofthe air in the turbulent flow region slightly away from the disk surface115. As is the case with the turbine, the relative velocity of the gasand surface approaches zero at the surface interface (laminar flowregion). It is therefore more difficult to rapidly transfer the air inthe laminar flow region. A compressor 210 therefore displaces the air inthe turbulent flow region, directly adjacent to the laminar flow regionat the surface. Slightly wider spaces between disks 102 are thereforeneeded for compressors 210 than for turbine expanders 230. FIGS. 17A and17B describe this in further detail below.

Upon leaving the vaned axial port 770 of the turbine expander 230 at thecenter of the impeller 700, the fluid is directed back to therecuperator 220 where it flows inside the creep-resistant thin-walledstainless steel tubes 650 in a double counter-flow mode and in closeproximity to the cooler compressed air in substantially parallel pathsinside the voids between the tubes 650. The entire flow path of thefluid is able to retain a streamlined spiral shape from the compressorinlet 350 through the turbine 230 through the recuperator 220 to theexhaust outlet 235.

FIG. 15A depicts a back plate 800 that is used in connected with thedisks 102 of the turbine expander 230 and the compressor 210. The backplate 800 has a central core 810 (which, in some embodiments, is member365), through which the shaft 110 can extend, and around which areconfigured the center axial vanes 366, which are preferably coupled tocore 810. Positioned around a face 820 of the back plate 800 arealigning rods, or fixing pins 525, that extend from the face 820 in adirection substantially parallel to a central axis of the central core810. In some embodiments, the core 810 preferably includes at least onespline 830 for increasing a friction fit between the core 810 and theshaft 110.

FIG. 15B illustrates an annular disk 102 that is configured to be usedin connection with the back plate 800 of FIG. 15A. The disk 102 includesa plurality of apertures 840, through which the aligning rods 525 of theback plate 800 may be inserted to orient the disk 102 with the backplate 800, the central core 810, and the center vanes 366. The disk 102further includes a central aperture 850 that can accommodate insertionof the central core 810 and center vanes 366. In some embodiments, thedisk 102 includes elevated portions 420 that can be shaped, in someembodiments, as an airfoil. Some embodiments provide that the elevatedportions 420 are the width of the boundary layer of the operating fluidwhen the turbine 200 is in use. FIGS. 16A and 16B depict a plurality ofdisks 102 assembled on a back plate 800 and described with reference toFIGS. 15A and 15B.

As discussed above, parameters that influence the performancecharacteristics of a disk turbine design, for example, a two stage diskturbine design, include a diameter, of compressor and turbine disks 102,the rotor speed, the gaps between the disks 102, the number of disks102, the shape of the spacers 420, and the inlet nozzle 744 design. Insome embodiments, the turbine 200 includes turbine impeller disks 102having a diameter of about 25 cm. In some embodiments, the turbineimpeller 700 can have disks 102 with diameters ranging from about 20 cmto about 30 cm. Some embodiments include a turbine impeller 700 withdisks 102 having diameters ranging from about 15 cm to about 35 cm, andsome embodiments include turbine impellers 700 with disks 102 havingdiameters less than about 15 cm or greater than about 35 cm.

In some embodiments, the turbine impeller 700 can include about 60disks. In some embodiments the turbine impeller 700 can have from about50 disks to about 70 disks, and in some embodiments, the turbineimpeller 700 can have from about 40 disks to about 80 disks. In someembodiments, the turbine impeller 700 can have less than about 40 disksor greater than about 80 disks.

In some embodiments, the number of turbine impeller disks 102 isdependent upon the number of compressor impeller disks 102, or thenumber of compressor disks 102 is determined by a ratio with respect tothe turbine disks 102, as discussed above. For example, in someembodiments the ratio of compressor disks to turbine expander disks isabout 2.5:1.

In some embodiments, the operational speed of the turbine impeller 700is the same as that of the shaft 110. In some embodiments, therotational speed of the turbine impeller 700 is about 20,000 rpm. Insome embodiments, the rotational speed of the turbine impeller 700ranges between about 15,000 rpm and about 25,000 rpm. In someembodiments, the rotational speed of the turbine impeller 700 rangesfrom about 10,000 rpm to about 30,000 rpm. In some embodiments, therotational speed of the turbine impeller 700 is less than about 10,000rpm or greater than about 30,000 rpm. For example, in some embodiments,the rotational speed of the turbine impeller 700 can be about 40,000rpm, about 50,000 rpm, about 75,000 rpm, and about 100,000 rpm.

In some embodiments, the turbine impeller disks 102 are spaced at adistance to enhance the efficiency of the turbine impeller 700. In someembodiments, the turbine impeller disks 102 are spaced about 0.6 mmapart. In some embodiments, the turbine impeller disks 102 are spacedbetween about 0.4 mm and about 0.8 mm apart, and in some embodiments,the turbine impeller disks 102 are spaced between about 0.2 mm and about1.0 mm apart. In some embodiments, the turbine impeller disks 102 arespaced less than about 0.2 mm or greater than about 1.0 mm apart.

FIGS. 17A-17B illustrate schematic representations of the flow past twodisks. The laminar flow regions are represented by D and E in FIG. 17A.In these regions, there is increased drag caused by the viscosity andadhesion properties of the fluid and the fluid throughout the boundarylayer is subjected to the shear stresses caused by free-flowing fluidoutside the boundary layer. The length A is the distance that the fluidflows along the surface of the disk. A space represented by Y representsa space through which the majority of flow passes with laminar flow, asdepicted in FIG. 17A. Energy is transferred to or from the disks via thelaminar flow boundary layer regions of FIG. 17A. When the disks are usedfor the compressor, the distance between the disks, X, is increased toallow turbulent fluid flow in the region B between the boundary layers.In FIGS. 17A and 17B, the majority of flow due to laminar flow occurs ina space represented by α. FIG. 17B illustrates the different in flowarea by separating the disks and permitting flow in the additional spacerepresented by B. In this turbulent region, the turbulent fluidintermixes and separates, increasing the kinetic energy of the air, tobe subsequently converted to pressure in the circumferential axial flowdiffuser. The continuous stream of separated fluid molecules arepropelled at high speeds into the circumferential diffuser, where theyare compressed with other fluid molecules and slow down, increasing thepressure. The pressure increase depends upon the velocity with which theair leaves the circumference of the disks.

The flow of compressed air is calculated as a positive displaced volumeof the active turbulent space between the disks. For maximum efficiencyin the turbine expander 230, the distance between the total boundarylayers, i.e., the laminar flow plus the turbulent flow regions, shouldbe zero (represented by the dotted rectangle below point B in FIG. 17A).When this distance becomes a minus number, inadequate space is presentedto the turbulent air to mix, resulting in undue slippage and a reductionin compressor efficiency. On the other hand, when the distance X is toolarge, as depicted by FIG. 17B, point B becomes greater than zero,introducing a doldrums effect, which dissipates the energy and reducesthe efficiency. For maximum efficiency in the expander 230 there shouldnot be any space between the two turbulent flow boundary layers, but thespace should be wide enough to include both turbulent flow regions.

FIG. 18 depicts the boundary layer effect turbine in connection withperipheral devices that can be used to control or regulate operation ofthe turbine 200. For example, illustrated in FIG. 18 is a power inverter863, power conditioning system 867, and turbine controls 869. Theseperipheral devices can be part of a single unit that includes theboundary layer effect turbine. FIGS. 19A and 19B respectively depict aschematic front view and rear view of the boundary layer effect turbine200, which highlight the compact configuration of the turbine 200.

FIGS. 20A-C depict a combustor 225, which accepts preheated air from therecuperator 220 in an air to fuel ratio of, for example, about 30:1 anda pressure of, for example, about 2.1 kPa. The combustor 225 comprises aprimary 910 and a secondary burner 915, the primary burner 910, whichrepresents the minimum operating capacity of 10%, is situated in thecenter. It is surrounded by a plurality of venturis 920 that are part ofthe secondary burners 915. The venturis 920 of the secondary burners 915draw fuel from a fuel line 927 at the rate determined by the flow of airthrough the throats 925 of the venturis 920. The venturis 920 therefore,in some embodiments, obviate the need for a separate gas compressor tocompress the fuel before injection into the combustor 225. The primaryburner 910 stabilizes the flames of the surrounding burners 915 andlikewise draws fuel from a primary fuel line 929, which can include anaxial fuel line 931. Excess air is bypassed around the burner casing tocool the casing before it is subsequently mixed with the hot gasemanating from the venturi burners. An annular excess air bypass controlsystem 936 facilitates burner management by either sending air throughthe venturis or bypass it around the combustor through, for example, aplurality of apertures 934. The shape of the burner casing acceleratesthe hot gas prior to entering the turbine expander 230. Also depicted isa spark plug 937 that can be used, in some embodiments, to ignite theburners.

The boundary layer effect turbine 200 described herein can be operatedon any credible form of combustible liquid or gaseous fuels, as long asthe burner arrangement and fuel air ratio are properly designed to matchthe specific fuel. It can further be utilized with natural sources ofheat, such as a geothermal source.

The boundary layer effect turbine 200, microturbine, or DiskTurbine© canalso run as an unfired turbine by sharing the same fuel supply with fuelcells, or it can be driven by the pressurized off gases of solid oxidefuel cells. In such applications, the combined power conversionefficiency could exceed 70%. The boundary layer effect turbine canoperate with various fuel cell technologies and fuel types, includingbut not limited to the following: bio-diesel, ethanol, natural gas,liquid propane gas, kerosene, diesel or any other gaseous or liquidhydrocarbon, coal bed methane or methane from municipal waste dumps(fuels are not universally interchangeable with the same burners) andoperates on renewable plant alcohol and oils or straight hydrogen. Forcoal fired applications, especially when poor quality coals are used,the coal can be fired in a fluidized bed combustor (FBC). Lime is addedto neutralize the sulfur to improve the chimney stack emission. Heatresistant heat exchanger tubes are inserted in the firing zone of theFBC and internally pressurized by the compressed air from thecompressor. The heated compressed air is allowed to expand in theturbine to generate power. The clean hot exhaust air is then used forspace heating, process heating, or steam generation for further powergeneration and/or HVAC.

Illustrated in FIGS. 21-24 are embodiments of a high speed reducer 1000that can be used in connection with turbines, for example, a boundarylayer effect microturbine 200, to transmit the rotary motion of theshaft 110. The high output speeds (usually more than about 20,000 up to100,000 rpm and more) at which microturbines operate makes the turbinesill-suited for applications other than power generation purposes. Use ofmicroturbines in automotive, marine, or aircraft applications can beproblematic because of limitations of roller type bearings and reductiongearboxes.

Provided in this disclosure is a high-speed hydrodynamic speed reducer1000 (“HSR”), which is aimed at operating with the microturbine toprovide a high-speed gearless speed reducers for microturbines in thesize range from about 80 hp to about 300 hp. For example, hybridpassenger vehicles may operate within this range.

The HSR 1000, illustrated in FIGS. 21 and 22, operates on thedisplacement of a special hydraulic fluid being recirculated at highspeeds between an inner drive and an outer multiple spiraled helix drive1010 and a single spiraled circumferential volute 1020. The volutecomprises an inside portion 1015 that has an outer diameter greater thanthe outer diameter of the volute 1020, such that the volute 1020 can beinserted into the inside portion 1015. Between the outer diameter of thevolute 1020 and the outer diameter of the insider portion 1015 of thehelix drive 1010 is positioned a sleeve 1030, such that, when assembled,the volute 1020 is positioned within the sleeve 1030, and the sleeve1030 is positioned within the inside portion 1015 of the helix drive1010. In some embodiments, the arrangement of the volute 1020, sleeve1030, and the drive 1010 are substantially concentric.

The volute 1020, sleeve 1030, and drive 1010 are preferably encased in acasing 1040 that can include a first portion 1045 and a second portion1050. The first and second portions 1045, 1050, when coupled togetherform a hollow interior, which is configured to contain the volute 1020,sleeve 1030, drive 1010, and operating oil. Each of the first and secondportions 1045, 1050 preferably accommodate coupling with a shaft. Insome embodiments, the first portion 1045 can include an aperture 1047through which an output shaft 1110 can extend. The output shaft 1110 canbe supported by a boss 1048 that contains a supporting bearing 1049. Insome embodiments, the second portion 1050 can be configured to couplewith embodiments of the turbine 200 described herein. In someembodiments, the second portion 1050 can include a plurality of fins1051 that disperse heat from the HSR 1000 and direct fluid flow into acompressor 210.

The helix drive 1010 conveys a specially designed synthetic oil axiallyalong the thread cavity of the inside portion 1015, the oil beingdischarged into the multiple spiraled volutes of an outer element overthe sleeve 1030, which is a concentric tubular divider. Four or morespiral shaped volutes of the outer element has only one spiral turn fromend to end. A constant volume of fluid, which is supplied by the volute1020, which operates as a worm drive, is divided equally between thenumber of spiral volutes, each volute having a similar cross sectionalarea as that of the volute 1020.

Should the combined cross sectional area of the drive and drivenelements be the same, the reduction ratio would have been 1:1. Byincreasing the number of spiral turns as well as the number of spirals,a reduction ratio of N×S is achieved, where N=the number of turns andS=the number of spirals, due to the fact that the number of spirals ofthe driven element is increased, causing the fluid to travel slowerthrough a combined cross sectional area which is now larger. It will beappreciated that a wide range of permutations is possible, depending onthe specific application, but the reduction ratio is fixed for eachpermutation.

The reaction forces that are created are axial in nature. The driveelement 1010 will tend to move to the opposite side the fluid would betraveling. Since the fluid is recirculated, it re-enters the driveelement 1010 at the bottom of the drive element 1010 to balance thataxial force. The same situation arises with the tubular divider, orsleeve 1030, which is being kept in an equilibrium position between thedrive, or volute 1020, and driven elements 1010. The driven element 1010will however tend to move axially towards the output shaft 1110. Tocounter that force, a slow speed thrust bearing may be fitted.

The output shaft 1110 is an inherent part of the driven element 1010.The bearing 1049 and seal cap, or boss 1048, keep the double thrustroller bearings in place. The driven element 1010 is shown with fourspiraled volutes each with a single turn. The geared teeth at the skirtof the driven element 1010 act as an oil pump to drive a smallpercentage of the oil to an external oil cooler via a tangential outlet.The volute 1020 is depicted with a single spiral with three turns,followed by the concentric tubular divider, or sleeve 1030. The maincasing is shown with its connecting fins 1051, which can also bestructural members to support the HSR 1000 and the compressor.

In some embodiments, the speed reducer 1000 includes a housing definingan internal chamber with a central axis, a cylindrical drive elementwithin the internal chamber, the drive element being aligned along thecentral axis and having a helical recess along an outer surface of thedrive element that defines a fluid drive flow path, the drive elementbeing configured to couple with a rotatable speed reducer input. Thespeed reducer can also include a driven element within the internalchamber, the driven element being aligned along the central axis andhaving a cylindrical bore with an internal surface having a helicalrecess that defines a fluid driven flow path. In some embodiments, thedriven element is configured to couple with a rotatable speed reduceroutput. In some embodiments, a tubular divider element within theinternal chamber and aligned along the central axis, the divider elementcan have a first end and a second end and being positioned between theouter surface of the cylindrical drive element and the internal surfaceof the driven element.

In some embodiments, the reducer 100 includes operating fluid within theinternal chamber, the fluid drive flow path, and the fluid driven flowpath, and rotation of the speed reducer output is achieved by rotatingthe speed reducer input, which rotates the drive element and drives theoperating fluid in a first axial direction along the fluid drive flowpath, around the first end of the tubular divider, in a second axialdirection along the fluid driven flow path, rotating the driven element,around the second end of the tubular divider, and into the fluid driveflow path.

At the heart of the system lies a magnetic drive 1018, which drives acentral element 1020, similar to a worm drive, and typically has threeor more spiral turns of adequate thread diameter. In order to isolatethe driven element from the high-speed shaft so as to eliminate the needfor a complex dynamic sealing arrangement, a magnetic drive is used.This drive has the capability of transferring mechanical power through anon-magnetic sleeve, making it possible to transfer horsepower from onecompartment to the adjacent one with out any physical contact.

FIGS. 23A and 23B depict embodiments of driving the main element,previously referred to as the volute 1020. Powerful permanent magnets1021 such as Alnico magnets, which possess a tolerance for temperaturesup to 300° C., are inserted with opposing poles into the drive element1020 in such a manner that they will be attracted by the powerfulpermanent magnets, which are inserted into the non-magnetic stainlesssteel drive shaft 110. The permanent magnets 1021 maintain theconcentricity of the drive shaft 110 and the drive element 1020 tomaintain a constant air gap 1022 around the shaft 110.

FIG. 24 depicts embodiments of the turbine 200 coupled to embodiments ofthe HSR 1000.

In some embodiments, the turbine 200 and HSR 1000 can be used inconnection with commercially available air conditioning systems 1100,such as that depicted in FIG. 25, which normally run on natural gas, butwhich can readily be adapted to use the exhaust gas of the turbine 200to provide free air conditioning and heating to commercial or industrialcomplexes. Overall thermal efficiencies of greater than 75% could beachieved, making the combination an environmentally preferred lowoperating cost system. In some embodiments, the system consists of areversible absorption heat pump unit for production of hot water up to140° F. and chilled water to 37.4° F., using waste energy. In someembodiments, extremely high energy efficiency can be achieved by meansof recovering 34% of the energy from the renewable source (air). It canbe, therefore, the best heating system for improving the energyefficiency of buildings. In some embodiments, with a single machine andsingle system it is also possible to provide air conditioning, byutilizing turbine exhaust waste heat. Some embodiments may be able toachieve an 87% reduction in electrical power requirement (0.75 kWe for120,400 BTU/h of heating output or 57,700 BTU/h of cooling output),compared with traditional electrical systems, since the primary energysource is free.

Although embodiments of the disclosure have been described in detail,certain variations and modifications will be apparent to those skilledin the art, including embodiments that do not provide all the featuresand benefits described herein. It will be understood by those skilled inthe art that the present disclosure extends beyond the specificallydisclosed embodiments to other alternative or additional embodimentsand/or uses and obvious modifications and equivalents thereof. Inaddition, while a number of variations have been shown and described invarying detail, other modifications, which are within the scope of thepresent disclosure, will be readily apparent to those of skill in theart based upon this disclosure. It is also contemplated that variouscombinations or sub-combinations of the specific features and aspects ofthe embodiments may be made and still fall within the scope of thepresent disclosure. Accordingly, it should be understood that variousfeatures and aspects of the disclosed embodiments can be combined withor substituted for one another in order to form varying modes of thepresent disclosure. Thus, it is intended that the scope of the presentdisclosure herein disclosed should not be limited by the particulardisclosed embodiments described above.

1. A modified boundary layer turbine, comprising: a housing having afluid inlet port and a fluid outlet port; a central shaft, extendingthrough the housing, the central shaft defining a central axis; aplurality of annular disks within the housing, each of the disks havinga face and being spaced apart from an adjacent disk such that the facesof the disks are substantially parallel; wherein each of the disks hasan outer edge, and an inner opening through which the central shaftextends; wherein the plurality of annular disks is configured in thehousing to transmit kinetic energy between at least one of the disks, asit rotates about the central shaft, and fluid introduced into thehousing through the fluid inlet port, the transmission of kinetic energyresulting, at least in part, from a boundary layer formed at the face ofat least one of the disks; and a plurality of elongate, arcuateelevations extending along the face of at least one of the disks, eachof the arcuate elevations having a first region and a second region;wherein the first region of each of the arcuate elevations is locatedcloser to the central axis than is the second region of the same arcuateelevation; and wherein each of the arcuate elevations tapers in width asit extends from the first region to the second region, such that a widthof each of the arcuate elevations at its first region is greater than awidth of the same arcuate elevation at its second region.
 2. Themodified boundary layer turbine of claim 1, wherein the arcuateelevation comprises substantially an airfoil shape.
 3. The modifiedboundary layer turbine of claim 1, wherein the arcuate elevation has athickness equal to about one-half of a space between adjacent disks. 4.The modified boundary layer turbine of claim 1, wherein the arcuateelevation has a thickness less than one-half of a space between adjacentdisks.
 5. The modified boundary layer turbine of claim 1, wherein,during rotation of the central shaft, the plurality of arcuateelevations directs fluid flowing across the face of the disk in aradially outward direction.
 6. The modified boundary layer turbine ofclaim 1, wherein, during rotation of the central shaft, the plurality ofarcuate elevations directs fluid flowing across the face of the disk ina radially inward direction.
 7. The modified boundary layer turbine ofclaim 1, wherein at least one of the arcuate elevations comprises athickness equal to about the thickness of a laminar flow boundary layerof a fluid that flows into the housing from the fluid inlet port andacross the face of at least one of the disks.
 8. The modified boundarylayer turbine of claim 1, wherein at least two of the disks with a spacebetween them equal to two boundary layer laminar flow thicknesses. 9.The modified boundary layer compressor of claim 1, wherein at least twoof the disks are spaced to allow air compression to take place in thefringe of the laminar flow zone.
 10. The modified boundary layer turbineof claim 1, wherein at least one of the arcuate elevations areintegrally formed with at least one of the plurality of annular disks.11. The modified boundary layer turbine of claim 1, wherein at least oneof the arcuate elevations comprises a different material than does theat least one of the disks.
 12. The modified boundary layer turbine ofclaim 1, wherein the central shaft is integral with a starter generatorand is supported by at least one magnetic bearing.
 13. The modifiedboundary layer turbine of claim 1, wherein the central shaft issupported by at least one air bearing.
 14. The modified boundary layerturbine of claim 1, further comprising a combustor having an annularexcess air bypass control system that facilitates combustion managementby sending air either through a plurality of venturi burners or througha bypass.
 15. A boundary layer turbine, comprising: a housing having afluid inlet port and a fluid outlet port; a central drive shaft,extending through a central portion of the housing, the central driveshaft defining a central axis; a plurality of annular disks, within thehousing, arrayed along and coupled to the central drive shaft; whereineach of the plurality of the annular disks has a front face and a rearface and is positioned along the central axis such that a plurality ofsubstantially parallel annular spaces is defined between adjacent facesof the plurality of the annular disks; wherein the plurality of theannular disks define a cylindrical space located central to inner edgesof the annular disks, the cylindrical space containing the central driveshaft; a blade member extending, in the cylindrical space, from thecentral drive shaft toward the inner edges of the annular disks, theblade member further extending helically about the central axis;wherein, during rotation of the central drive shaft, fluid located inthe annular spaces is drawn in the direction of rotation in a boundarylayer within the annular spaces; and wherein, during rotation of thecentral drive shaft, fluid in the cylindrical space is received alongthe cylindrical space from the fluid inlet port and directed radiallyoutwardly through the annular spaces.
 16. The boundary layer turbine ofclaim 15, wherein the blade member has width that extends from aninterior edge of the blade member, located adjacent the central shaft,to an outer edge of the blade member that is closer to at least one ofthe plurality of the annular disks than is the interior edge; whereinthe blade member is curved along its width.
 17. The boundary layerturbine of claim 15, wherein the inner edge of at least one of theplurality of the annular disks is tapered.
 18. The boundary layerturbine of claim 15, wherein an outer edge of at least one of theplurality of the annular disks is tapered.
 19. The boundary layerturbine of claim 18, wherein the inner edge of the at least one of theplurality of the annular disks is tapered.
 20. The boundary layerturbine of claim 15, wherein at least one of the plurality of theannular disks comprises a plurality of elongate, arcuate elevationsextending along the face of the at least one of the disks, each of thearcuate elevations having a first region and a second region; whereinthe first region of each of the arcuate elevations is located closer tothe central axis than is the second region of the same arcuateelevation; and wherein each of the arcuate elevations tapers in width asit extends from the first region to the second region, such that a widthof each of the arcuate elevations at its first region is greater than awidth of the same arcuate elevation at its second region.
 21. Theboundary layer turbine of claim 15, further comprising a plurality ofblade members extending, in the cylindrical space, from the centraldrive shaft toward the inner edges of the annular disks, each of theplurality of blade members further extending helically about the centralaxis.
 22. The modified boundary layer turbine of claim 15, wherein thecentral shaft is supported, during rotation, by at least one magneticbearing.
 23. The modified boundary layer turbine of claim 15, whereinthe central shaft is supported, during rotation, by at least one airbearing.
 24. A disk turbine impeller, comprising: a plurality ofsubstantially parallel annular disks, axially spaced along a rotationaxis, the annular disks defining a cylindrical space extending through acenter portion of the annular disks and bounded by inner edges of theannular disks; wherein the plurality of annular disks define a pluralityof annular spaces between adjacent of the annular disks; and a pluralityof axial vanes that extend, within the cylindrical space, toward theinner edges of the annular disks from the rotation axis; wherein theaxial vanes are oriented helically about the rotation axis.
 25. The diskturbine assembly of claim 24, wherein the blade member has width thatextends from an interior edge of the blade member, located adjacent therotation axis, to an outer edge of the blade member that is closer to atleast one of the plurality of the annular disks than is the interioredge; wherein the blade member is curved along its width.
 26. The diskturbine assembly of claim 24, wherein the inner edge of at least one ofthe plurality of the annular disks is tapered.
 27. The disk turbineassembly of claim 24, wherein an outer edge of at least one of theplurality of the annular disks is tapered.
 28. The disk turbine assemblyof claim 27, wherein the inner edge of the at least one of the pluralityof the annular disks is tapered.
 29. The disk turbine assembly of claim24, wherein at least one of the plurality of the annular disks comprisesa plurality of elongate, arcuate elevations extending along a face ofthe at least one of the disks, each of the arcuate elevations having afirst region and a second region; wherein the first region of each ofthe arcuate elevations is located closer to the rotation axis than isthe second region of the same arcuate elevation; and wherein each of thearcuate elevations tapers in width as it extends from the first regionto the second region, such that a width of each of the arcuateelevations at its first region is greater than a width of the samearcuate elevation at its second region.
 30. The disk turbine assembly ofclaim 24, further comprising a plurality of blade members extending, inthe cylindrical space, from the rotation axis toward the inner edges ofthe annular disks, each of the plurality of blade members furtherextending helically about the rotation axis.